diff options
Diffstat (limited to '548')
217 files changed, 1972 insertions, 0 deletions
diff --git a/548/CH10/EX10.1/10_01.sce b/548/CH10/EX10.1/10_01.sce new file mode 100755 index 000000000..1108f7849 --- /dev/null +++ b/548/CH10/EX10.1/10_01.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('10_01.sce')
+filename=pathname+filesep()+'10_01data.sci'
+exec(filename)
+dl=strain*l;disp(dl,"dl=","dl=strain*l","elongation of the rod dl:")
+printf("\Answer:\n")
+printf("\n\elongation of the rod under this load: %f m\n\n",dl)
diff --git a/548/CH10/EX10.2/10_02.sce b/548/CH10/EX10.2/10_02.sce new file mode 100755 index 000000000..54a100182 --- /dev/null +++ b/548/CH10/EX10.2/10_02.sce @@ -0,0 +1,4 @@ +pathname=get_absolute_file_path('10_02.sce')
+filename=pathname+filesep()+'10_02data.sci'
+exec(filename)
+disp("as the applied stress (approx 3513) bar is greater than yield stress but less than ultimate stress of the aluminium rod,it will experience permanent set but will not fracture" )
\ No newline at end of file diff --git a/548/CH11/EX11.1/11_01.sce b/548/CH11/EX11.1/11_01.sce new file mode 100755 index 000000000..65b8e80ad --- /dev/null +++ b/548/CH11/EX11.1/11_01.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('11_01.sce')
+filename=pathname+filesep()+'11_01data.sci'
+exec(filename)
+Cp=Cpmax*(sin(theta))^2;
+disp(Cp,"Cp=","Cp=Cpmax*(sin(theta))^2","pressure coefficient at point 1 Cp:")
+printf("\Answer:\n")
+printf("\n\pressure coefficient at point 1 : %f \n\n",Cp)
diff --git a/548/CH2/EX2.1/2_1.sce b/548/CH2/EX2.1/2_1.sce new file mode 100755 index 000000000..dcb8da7a1 --- /dev/null +++ b/548/CH2/EX2.1/2_1.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('2_1.sce')
+filename=pathname+filesep()+'2_1data.sci'
+exec(filename)
+T=p/((density)*(R))
+printf("\Answer:\n")
+printf("\n\Temperature at that point %f K\n\n",T)
diff --git a/548/CH2/EX2.2/2_2.sce b/548/CH2/EX2.2/2_2.sce new file mode 100755 index 000000000..da338be8e --- /dev/null +++ b/548/CH2/EX2.2/2_2.sce @@ -0,0 +1,5 @@ +pathname=get_absolute_file_path('2_2.sce')
+filename=pathname+filesep()+'2_2data.sci'
+exec(filename)
+
+disp(M,"Mass in Kg",M1,"Mass in pound");
\ No newline at end of file diff --git a/548/CH2/EX2.3/2_3.sce b/548/CH2/EX2.3/2_3.sce new file mode 100755 index 000000000..6242ebb70 --- /dev/null +++ b/548/CH2/EX2.3/2_3.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('2_3.sce')
+filename=pathname+filesep()+'2_3data.sci'
+exec(filename)
+density=P/(R*T);
+v=1/density;//specific volume
+printf("\Answer:\n")
+printf("\n\Density of air: %f Kg/m^3\n\n",density)
+printf("\n\Specific volume of air: %f m^3/Kg\n\n",v)
+
+
diff --git a/548/CH2/EX2.4/2_4.sce b/548/CH2/EX2.4/2_4.sce new file mode 100755 index 000000000..bb03bb34a --- /dev/null +++ b/548/CH2/EX2.4/2_4.sce @@ -0,0 +1,5 @@ +pathname=get_absolute_file_path('2_4.sce')
+filename=pathname+filesep()+'2_4data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\Density of air at the given point: %f Kg/m^3\n\n",density)
\ No newline at end of file diff --git a/548/CH2/EX2.5/2_5.sce b/548/CH2/EX2.5/2_5.sce new file mode 100755 index 000000000..78946b5c9 --- /dev/null +++ b/548/CH2/EX2.5/2_5.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('2_5.sce')
+filename=pathname+filesep()+'2_5data.sci'
+exec(filename)
+function[unit]=Conversion(SI)
+ unit=(9.8*(0.3048)^2)*(SI)/4.448;
+ endfunction
+ disp("1lb/ft^2=(9.8*(0.3048)^2)*/4.448)kgf/m^2")
+ disp(Conversion(280.8),"wing loading in lb/ft^2 for F-117A stealth fighter");
\ No newline at end of file diff --git a/548/CH2/EX2.6/2_6.sce b/548/CH2/EX2.6/2_6.sce new file mode 100755 index 000000000..71080b48c --- /dev/null +++ b/548/CH2/EX2.6/2_6.sce @@ -0,0 +1,17 @@ +pathname=get_absolute_file_path('2_6.sce')
+filename=pathname+filesep()+'2_6data.sci'
+exec(filename)
+function[ftPerSecond]=conversion(MilePerHour)
+ ftPerSecond=(5280*MilePerHour)/3600;
+endfunction
+function[meterPerSecond]=conversion1(MilePerHour)
+ meterPerSecond=(1609.344*MilePerHour)/3600;
+endfunction
+disp("1 ftPerSecond=(5280*MilePerHour)/3600")
+
+disp(conversion(60),"velocity in terms of ft/s");
+
+disp("1 meterPerSecond=(1609.344*MilePerHour)/3600")
+disp(conversion1(60),"velocity in terms of m/s");
+
+
diff --git a/548/CH3/EX3.01/3_01.sce b/548/CH3/EX3.01/3_01.sce new file mode 100755 index 000000000..dfb69c8eb --- /dev/null +++ b/548/CH3/EX3.01/3_01.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('3_01.sce')
+filename=pathname+filesep()+'3_01data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\pressure at an altitude of 14 Km: %f N/m^2\n",P2)
+printf("\n\density at an altitude of 14 Km: %f Kg/m^3\n\n",D2)
+
diff --git a/548/CH3/EX3.02/3_02.sce b/548/CH3/EX3.02/3_02.sce new file mode 100755 index 000000000..08712edb3 --- /dev/null +++ b/548/CH3/EX3.02/3_02.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('3_02.sce')
+filename=pathname+filesep()+'3_02data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\pressure altitude: %f Km\n\n",P1)
+printf("\n\ temperature altitude: %f Km\n\n",T1)
+printf("\n\density altitude: %f Km\n\n",D1)
+
diff --git a/548/CH3/EX3.03/3_03.sce b/548/CH3/EX3.03/3_03.sce new file mode 100755 index 000000000..3bf6195fe --- /dev/null +++ b/548/CH3/EX3.03/3_03.sce @@ -0,0 +1,5 @@ +pathname=get_absolute_file_path('3_03.sce')
+filename=pathname+filesep()+'3_03data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\Temperature of air at flying altitude of airplane: %f K\n\n",T)
\ No newline at end of file diff --git a/548/CH3/EX3.04/3_04.sce b/548/CH3/EX3.04/3_04.sce new file mode 100755 index 000000000..8f7a5df1f --- /dev/null +++ b/548/CH3/EX3.04/3_04.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('3_04.sce')
+filename=pathname+filesep()+'3_04data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\pressur altitude: %f Km\n",Hp)
+printf("\n\density altitude : %f Km\n\n",Hd)
diff --git a/548/CH4/EX4.01/4_01.sce b/548/CH4/EX4.01/4_01.sce new file mode 100755 index 000000000..a29414dbc --- /dev/null +++ b/548/CH4/EX4.01/4_01.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('4_01.sce')
+filename=pathname+filesep()+'4_01data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\area of the duct exit: %f m^2\n\n",A2)
+
diff --git a/548/CH4/EX4.02/4_02.sce b/548/CH4/EX4.02/4_02.sce new file mode 100755 index 000000000..6f6c5b37f --- /dev/null +++ b/548/CH4/EX4.02/4_02.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('4_02.sce')
+filename=pathname+filesep()+'4_02data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\density of air at the duct exit: %f Kg/m^3\n\n",D2)
+
diff --git a/548/CH4/EX4.03/4_03.sce b/548/CH4/EX4.03/4_03.sce new file mode 100755 index 000000000..e971c68a1 --- /dev/null +++ b/548/CH4/EX4.03/4_03.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('4_03.sce')
+filename=pathname+filesep()+'4_03data.sci'
+exec(filename)
+disp("P1+(D*V1^2/2)=Pa+(D*Va^2/2)","Bernoulli equation");
+Va=[(2*(P1-Pa)/D)+(V1)^2]^0.5;disp(Va,"Va=")
+printf("\Answer:\n")
+printf("\n\velocity at a point A on airfoil: %f m/s\n\n",Va)
+
diff --git a/548/CH4/EX4.04/4_04.sce b/548/CH4/EX4.04/4_04.sce new file mode 100755 index 000000000..acbbf27c5 --- /dev/null +++ b/548/CH4/EX4.04/4_04.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('4_04.sce')
+filename=pathname+filesep()+'4_04data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\pressure at the duct exit: %f N/m^2\n\n",P2)
+
diff --git a/548/CH4/EX4.05/4_05.sce b/548/CH4/EX4.05/4_05.sce new file mode 100755 index 000000000..ad997bcba --- /dev/null +++ b/548/CH4/EX4.05/4_05.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('4_05.sce')
+filename=pathname+filesep()+'4_05data.sci'
+exec(filename)
+D=1.067*D*V^2*R;
+printf("\Answer:\n")
+printf("\n\Aerodynamic force exerted by surface pressure distribution: %f N\n\n",D)
diff --git a/548/CH4/EX4.06/4_06.sce b/548/CH4/EX4.06/4_06.sce new file mode 100755 index 000000000..6d9163d6e --- /dev/null +++ b/548/CH4/EX4.06/4_06.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_06.sce')
+filename=pathname+filesep()+'4_06data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\internal energy per unit mass in SI unit: %f J/Kg.K\n\n",e)
+printf("\n\internal energy per unit mass in English enginering unit: %f Ft.Lb/slug\n\n",e1)
+printf("\n\enthalpy per unit mass in SI unit: %f J/Kg.K\n\n",h)
+printf("\n\enthalpy per unit mass in English enginering unit: %f Ft.Lb/slug\n\n",h1)
+
+
diff --git a/548/CH4/EX4.07/4_07.sce b/548/CH4/EX4.07/4_07.sce new file mode 100755 index 000000000..1ef37203f --- /dev/null +++ b/548/CH4/EX4.07/4_07.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_07.sce')
+filename=pathname+filesep()+'4_07data.sci'
+exec(filename)
+disp("P2/P1=(T2/T1)^y/y-1","For isentropic flow","let P2 be the pressure at that point of wing");
+P2=P1*(T/T1)^(y/(y-1));disp(P2,"P2=")
+printf("\Answer:\n")
+printf("\n\Pressure at this point: %f N/m^2\n\n",P2)
diff --git a/548/CH4/EX4.08/4_08.sce b/548/CH4/EX4.08/4_08.sce new file mode 100755 index 000000000..3330b335e --- /dev/null +++ b/548/CH4/EX4.08/4_08.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_08.sce')
+filename=pathname+filesep()+'4_08data.sci'
+exec(filename)
+disp("T2=T1*(P2/P1)^((y-1)/y)","from isentropic condition:")
+T2=T1*(P2/P1)^((y-1)/y)//temperature at exit
+printf("\Answer:\n")
+printf("\n\Gas temperature at the exit: %f K\n\n",T2)
diff --git a/548/CH4/EX4.09/4_09.sce b/548/CH4/EX4.09/4_09.sce new file mode 100755 index 000000000..908c40108 --- /dev/null +++ b/548/CH4/EX4.09/4_09.sce @@ -0,0 +1,18 @@ +pathname=get_absolute_file_path('4_09.sce')
+filename=pathname+filesep()+'4_09data.sci'
+exec(filename)
+disp("So V1^2=2Cp*(To-T1)","CpTo=CpT1+(V1^2)/2","From energy equation:","let V1 be the velocity of throat")
+V1=(2*Cp*(To-T1))^0.5;
+printf("\n\Velocity at throat: %f m/s\n\n",V1)
+disp("So Ve^2=2Cp*(To-Te)","CpTo=CpTe+(Ve^2)/2","From energy equation:","let Ve be the velocity of exit")
+Ve=(2*Cp*(To-Te))^0.5;
+printf("\n\Velocity at the exit: %f m/s\n\n",Ve)
+disp("A1=Mt/(D1*V1)","Area of throat")
+A1=Mt/(D1*V1);
+printf("\n\Area of throat: %f m^2\n\n",A1)
+disp("Ae=Mt/(De*Ve)","Area of the exit")
+Ae=Mt/(De*Ve);
+printf("\n\Area of the exit: %f m^2\n\n",Ae)
+
+
+
diff --git a/548/CH4/EX4.10/4_10.sce b/548/CH4/EX4.10/4_10.sce new file mode 100755 index 000000000..db4b2b2f4 --- /dev/null +++ b/548/CH4/EX4.10/4_10.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_10.sce')
+filename=pathname+filesep()+'4_10data.sci'
+exec(filename)
+disp("So Va^2=2Cp*(T-Ta)+V^2","CpT+(V^2)/2=CpTa+(Va^2)/2","From energy equation:","let Va be the velocity of the point A")
+Va=(2*Cp*(T-Ta)+V^2)^0.5;disp(Va,"Va=")
+printf("\Answer:\n")
+printf("\n\Velocity at point A: %f m/s\n\n",Va)
diff --git a/548/CH4/EX4.11/4_11.sce b/548/CH4/EX4.11/4_11.sce new file mode 100755 index 000000000..1606f6d64 --- /dev/null +++ b/548/CH4/EX4.11/4_11.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_11.sce')
+filename=pathname+filesep()+'4_11data.sci'
+exec(filename)
+disp("Mach No M=V/a");
+M=V/a;disp(M,"M=")
+printf("\Answer:\n")
+printf("\n\Mach No of the jet transport: %f\n\n",M)
\ No newline at end of file diff --git a/548/CH4/EX4.12/4_12.sce b/548/CH4/EX4.12/4_12.sce new file mode 100755 index 000000000..80fe1ff55 --- /dev/null +++ b/548/CH4/EX4.12/4_12.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_12.sce')
+filename=pathname+filesep()+'4_12data.sci'
+exec(filename)
+disp("Mach No at Throat Mt=V1/a");
+Mt=V1/a;disp(Mt,"Mt=")
+disp("Mach No at Throat Me=Ve/Ae");
+Me=Ve/Ae;disp(Me,"Me=")
+printf("\Answer:\n")
+printf("\n\Mach No at throat: %f\n\n",Mt)
+printf("\n\Mach No at exit: %f\n\n",Me)
\ No newline at end of file diff --git a/548/CH4/EX4.13/4_13.sce b/548/CH4/EX4.13/4_13.sce new file mode 100755 index 000000000..4730c0e1d --- /dev/null +++ b/548/CH4/EX4.13/4_13.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_13.sce')
+filename=pathname+filesep()+'4_13data.sci'
+exec(filename)
+disp("(2(P1-P2)/(D1(1-(A2/A1)^2)))^0.5=(2*(Dp)/(D1*(1-r^2)))^0.5","Airflow velocity at test section V=");
+V=(2*(Dp)/(D1*(1-r^2)))^0.5;disp(V,"V=");
+printf("\Answer:\n")
+printf("\n\Airflow velocity in the test section: %f m/s\n\n",V)
diff --git a/548/CH4/EX4.14/4_14.sce b/548/CH4/EX4.14/4_14.sce new file mode 100755 index 000000000..48f752179 --- /dev/null +++ b/548/CH4/EX4.14/4_14.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_14.sce')
+filename=pathname+filesep()+'4_14data.sci'
+exec(filename)
+disp("P2+D(V2^2-V1^2)/2","pressure at reservoir P1=")
+P1=P2+D*(V2^2-V1^2)/2;disp(P1,"P1=")
+disp("Mt=D*A1*V1","mass flow rate :")
+Mt=D*A1*V1;disp(Mt,"Mt=")
+printf("\Answer:\n")
+printf("\n\pressure required to have a velocity of 40 m/s at test section: %f N/m^2\n\n",P1)
+printf("\n\mass flow through the wind tunnel: %f Kg/s\n\n",Mt)
diff --git a/548/CH4/EX4.15/4_15.sce b/548/CH4/EX4.15/4_15.sce new file mode 100755 index 000000000..60a0071b9 --- /dev/null +++ b/548/CH4/EX4.15/4_15.sce @@ -0,0 +1,11 @@ +pathname=get_absolute_file_path('4_15.sce')
+filename=pathname+filesep()+'4_15data.sci'
+exec(filename)
+disp("V2 propertional to (P2-P1)^0.5","velocity in test section is propertional to square root of pressure difference")
+V2=(40)*2^(0.5);disp(V2,"velocity after pressure difference is doubled is squareroot 2 times 40")
+disp("(2(P1-P2)/(D(1-(A2/A1)^2)))^0.5=(2*(Dp)/(D*(1-(1/R)^2)))^0.5","Airflow velocity at test section V3=");
+V3=(2*(Dp)/(D*(1-(1/R)^2)))^0.5;disp(V3,"V3=");
+printf("\Answer:\n")
+printf("\n\Airflow velocity in the test section after doubling pressure difference: %f m/s\n\n",V2)
+printf("\n\Airflow velocity in the test section after doubling contraction ratio: %f m/s\n\n",V3)
+
diff --git a/548/CH4/EX4.16/4_16.sce b/548/CH4/EX4.16/4_16.sce new file mode 100755 index 000000000..601272339 --- /dev/null +++ b/548/CH4/EX4.16/4_16.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_16.sce')
+filename=pathname+filesep()+'4_16data.sci'
+exec(filename)
+disp("Vt=(2(Po-P)/D)^0.5","True velocity of airplane")
+Vt=sqrt(2*(Po-P)/D);disp(Vt,"Vt=");
+disp("Ve=(2(Po-P)/Ds)^0.5","Eqivalent airspeed of airplane")
+Ve=sqrt(2*(Po-P)/Ds);disp(Ve,"Ve=");
+printf("\Answer:\n")
+printf("\n\True velocity of the airplane: %f m/s\n\n",Vt)
+printf("\n\Equivalent airspeed of the airplane: %f m/s\n\n",Ve)
diff --git a/548/CH4/EX4.17/4_17.sce b/548/CH4/EX4.17/4_17.sce new file mode 100755 index 000000000..f20d54ff9 --- /dev/null +++ b/548/CH4/EX4.17/4_17.sce @@ -0,0 +1,15 @@ +pathname=get_absolute_file_path('4_17.sce')
+filename=pathname+filesep()+'4_17data.sci'
+exec(filename)
+disp("M1^2=2*[(Po/P1)^((y-1)/y)-1]/(y-1))","let Mach no at which the airplane flying is M1 then")
+M1=sqrt(2*[(Po/P1)^((y-1)/y)-1]/(y-1));disp(M1,"M1=");
+a1=sqrt(y*R*T);disp(a1,"a1=(y*R*T)^0.5","speed of sound at that point");
+V1=sqrt(2*a1^2*[(Po/P1)^((y-1)/y)-1]/(y-1));
+disp(V1,"V1=","V1^2=2*a1^2*[(Po/P1)^((y-1)/y)-1]/(y-1)","equvalent air speed V1")
+R=((y-1)/y);
+Vc=sqrt([2*a^2*[(((Po-P1)/P)+1)^((y-1)/y)-1]/(y-1)]);
+disp(Vc,"Vc=","Vc^2=2*a^2*[((Po-P1)/P)+1)^((y-1)/y)-1]/(y-1)","caliberated air speed Vc")
+printf("\Answer:\n")
+printf("\n\mach no at which airplane is flying: %f \n\n",M1)
+printf("\n\True airspeed of the airplane: %f m/s\n\n",V1)
+printf("\n\caliberated airspeed of the airplane: %f m/s\n\n",Vc)
diff --git a/548/CH4/EX4.18/4_18.sce b/548/CH4/EX4.18/4_18.sce new file mode 100755 index 000000000..8edfc1096 --- /dev/null +++ b/548/CH4/EX4.18/4_18.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('4_18.sce')
+filename=pathname+filesep()+'4_18data.sci'
+exec(filename)
+Po=P*[(y+1)^2*M^2/((4*y*M^2)-2*(y-1))]^3.5*(1-y+2*y*M^2)/(y+1)
+disp("Po=P1*[(y+1)^2*M^2/((4*y*M^2)-2*(y-1))]^3.5*(1-y+2*y*M^2)/(y+1)","pressure measured by pitot tube Po")
+printf("\Answer:\n")
+printf("\n\pressure measured by pitot tube: %f N/m^2\n\n",Po)
diff --git a/548/CH4/EX4.19/4_19.sce b/548/CH4/EX4.19/4_19.sce new file mode 100755 index 000000000..10721596c --- /dev/null +++ b/548/CH4/EX4.19/4_19.sce @@ -0,0 +1,11 @@ +pathname=get_absolute_file_path('4_19.sce')
+filename=pathname+filesep()+'4_19data.sci'
+exec(filename)
+Ma=[[(Po/Pa)^((y-1)/y)-1]*2/(y-1)]^0.5;disp(Ma,"Ma=","Ma=[(Po/Pa)^((y-1)/y)-1]*2/(y-1)","Mach no at point A")
+Ta=Toa/[1+(y-1)*Ma^2/2];
+disp(Ta,"Ta=","Ta=Toa/[1+(y-1)*Ma^2/2]","static temperature at A")
+Va=sqrt(y*R*Ta)*Ma;
+disp(Va,"Va=","velocity at A =a*Ma,where a(sqrt(y*R*Ta)) is apeed of sound at A")
+printf("\Answer:\n")
+printf("\n\Mach No at A: %f \n\n",Ma)
+printf("\n\velocity at A: %f m/s\n\n",Va)
diff --git a/548/CH4/EX4.20/4_20.sce b/548/CH4/EX4.20/4_20.sce new file mode 100755 index 000000000..2d375c7eb --- /dev/null +++ b/548/CH4/EX4.20/4_20.sce @@ -0,0 +1,15 @@ +pathname=get_absolute_file_path('4_20.sce')
+filename=pathname+filesep()+'4_20data.sci'
+exec(filename)
+To=Te*A
+disp(To,"To=","To=Te*(1+(y-1)*Me^2/2)","let reservoir temperature required is To ")
+Po=Pe*A^(y/(y-1));
+disp(Po,"Po=","Po=Pe*((1+(y-1)*Me^2/2))^y/y-1","let reservoir pressure required is Po ")
+r=sqrt((2*A/(y+1))^((y+1)/(y-1))/Me^2)
+disp(r,"Ae/At=","Ae/At=sqrt((2*(1+(y-1)*Me^2/2)/(y+1))^((y+1)/(y-1))/Me^2","Area ratio required is equal to")
+printf("\Answer:\n")
+printf("\n\ required reservoir temperature: %f K\n\n",To)
+printf("\n\ required reservoir pressure: %f N/m^2\n\n",Po)
+printf("\n\ required Area Ratio: %f \n\n",r)
+
+
diff --git a/548/CH4/EX4.21/4_21.sce b/548/CH4/EX4.21/4_21.sce new file mode 100755 index 000000000..7b888a619 --- /dev/null +++ b/548/CH4/EX4.21/4_21.sce @@ -0,0 +1,12 @@ +pathname=get_absolute_file_path('4_21.sce')
+filename=pathname+filesep()+'4_21data.sci'
+exec(filename)
+Pstag=Pe*[(y+1)^2*Me^2/((4*y*Me^2)-2*(y-1))]^(y/(y-1))*(1-y+2*y*Me^2)/(y+1)
+disp(Pstag,"Pstag=","Pstag=Pe*[(y+1)*Me^2/((4*y*Me^2)-2*(y-1))]^(y/(y-1))*(1-y+2*y*Me^2)/(y+1)","the stagnation presure is given by Pstag")
+Dstag=Pstag/(R*Tstag);
+disp(Dstag,"Dstag=","Dstag=Pstag/(R*Tstag)","the stagnation density is given by Dstag")
+printf("\Answer:\n")
+printf("\n\ Stagnation temperature: %f K\n\n",Tstag)
+printf("\n\ Stagnation pressure: %f N/m^2\n\n",Pstag)
+printf("\n\ Stagnation density: %f Kg/m^3\n\n",Dstag)
+
diff --git a/548/CH4/EX4.22/4_22.sce b/548/CH4/EX4.22/4_22.sce new file mode 100755 index 000000000..130e026dd --- /dev/null +++ b/548/CH4/EX4.22/4_22.sce @@ -0,0 +1,9 @@ +pathname=get_absolute_file_path('4_22.sce')
+filename=pathname+filesep()+'4_22data.sci'
+exec(filename)
+Ve=Ae*Me;disp(Ve,"Ve=","velocity at exit Ve=Ae*Me")
+Mt=Dt*At*Vt;disp(Mt,"Mt=Dt*At*Vt","mass flow through nozzle Mt")
+printf("\Answer:\n")
+printf("\n\Velocity at exit: %f m/s\n\n",Ve)
+printf("\n\mass flow through nozzle: %f Kg/m^3\n\n",Mt)
+
diff --git a/548/CH4/EX4.23/4_23.sce b/548/CH4/EX4.23/4_23.sce new file mode 100755 index 000000000..6949698a0 --- /dev/null +++ b/548/CH4/EX4.23/4_23.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_23.sce')
+filename=pathname+filesep()+'4_23data.sci'
+exec(filename)
+t=5.2*x/Re^0.5;disp(t,"t=","boundary layer thickness t=5.2*x/Re^0.5")
+D=q*S*Cf;disp(D,"D=","drag on one surface of the plate given by D=q*s*Cf")
+disp(2*D,"Dn=","Net drag Dn is two times both surface i.e 2D")
+printf("\Answer:\n")
+printf("\n\Boundary layer thickness at downstream edge: %f m\n\n",t)
+printf("\n\The drag force on plate: %f N\n\n",2*D)
+
diff --git a/548/CH4/EX4.24/4_24.sce b/548/CH4/EX4.24/4_24.sce new file mode 100755 index 000000000..3f15b3c0a --- /dev/null +++ b/548/CH4/EX4.24/4_24.sce @@ -0,0 +1,9 @@ +pathname=get_absolute_file_path('4_24.sce')
+filename=pathname+filesep()+'4_24data.sci'
+exec(filename)
+Tw1=q*Cf1;disp(Tw1,"Tw1=","Tw1=q*Cf1","shear stress at 1 cm Tw1:");
+Tw2=q*Cf2;disp(Tw2,"Tw2=","Tw2=q*Cf2","shear stress at 1 cm Tw2:");
+printf("\Answer:\n")
+printf("\n\Local shear stress at 1 cm: %f N/m^2\n\n",Tw1)
+printf("\n\Local shear stress at 5 cm: %f N/m^2",Tw2)
+disp("Hence Tw decreases with distance in flow direction");
diff --git a/548/CH4/EX4.25/4_25.sce b/548/CH4/EX4.25/4_25.sce new file mode 100755 index 000000000..5b084bf5e --- /dev/null +++ b/548/CH4/EX4.25/4_25.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('4_25.sce')
+filename=pathname+filesep()+'4_25data.sci'
+exec(filename)
+T=0.37*x/Re^0.2;disp(T,"T=","T=0.37*x/Re^0.2","Thickness at trailing edge T:");
+Df=q*S*Cf;disp(Df,"Df=","Df=q*S*Cf","Drag at top surface")
+printf("\Answer:\n")
+printf("\n\Thickness at trailing edge: %f m\n\n",T)
+printf("\n\Total Drag: %f N",2*Df)
diff --git a/548/CH4/EX4.26/4_26.sce b/548/CH4/EX4.26/4_26.sce new file mode 100755 index 000000000..a6f53b3a5 --- /dev/null +++ b/548/CH4/EX4.26/4_26.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('4_26.sce')
+filename=pathname+filesep()+'4_26data.sci'
+exec(filename)
+Tw1=q*Cf1;disp(Tw1,"Tw1=","Tw1=q*Cf1","shear stress at 1 cm Tw1:");
+Tw2=q*Cf2;disp(Tw2,"Tw2=","Tw2=q*Cf2","shear stress at 1 cm Tw2:");
+printf("\Answer:\n")
+printf("\n\Local shear stress at 1 cm: %f N/m^2\n\n",Tw1)
+printf("\n\Local shear stress at 5 cm: %f N/m^2",Tw2)
diff --git a/548/CH4/EX4.27/4_27.sce b/548/CH4/EX4.27/4_27.sce new file mode 100755 index 000000000..60f8a7e8c --- /dev/null +++ b/548/CH4/EX4.27/4_27.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('4_27.sce')
+filename=pathname+filesep()+'4_27data.sci'
+exec(filename)
+Tw=q*Cf;disp(Tw,"Tw=","Tw=q*Cf","shear stress at point 0.6096 m Tw:");
+printf("\Answer:\n")
+printf("\n\shear stress at a point 0.6096m downstream of the leading edge: %f m\n\n",Tw)
diff --git a/548/CH4/EX4.28/4_28.sce b/548/CH4/EX4.28/4_28.sce new file mode 100755 index 000000000..214d6c3e4 --- /dev/null +++ b/548/CH4/EX4.28/4_28.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('4_28.sce')
+filename=pathname+filesep()+'4_28data.sci'
+exec(filename)
+Ds=q*S*0.074/Re^0.2;disp(Ds,"Ds=","Ds=q*S*0.074/Re^0.2","turbulent drag over complete area(A+B)");
+Da=q*A*0.074/Ret^0.2;disp(Da,"Da=","Da=q*A*0.074/Ret^0.2","turbulent drag over area A");
+disp(Ds-Da,"Db=","turbulent drag over area B Db:");Db=Ds-Da;
+Dl=q*A*1.328/Ret^0.5;disp(Dl,"Dl=","Dl=q*A*1.328/Ret^0.5","laminar drag over area A");
+Dn=Db+Dl;disp(Dn,"Dn=","Dn=Db+Dl","Net drag Dn")
+printf("\Answer:\n")
+printf("\n\Skin friction Drag over wings of biplane(4 surfaces): %f N\n\n",4*Dn)
diff --git a/548/CH5/EX5.01/5_01.sce b/548/CH5/EX5.01/5_01.sce new file mode 100755 index 000000000..e7e1be089 --- /dev/null +++ b/548/CH5/EX5.01/5_01.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('5_01.sce')
+filename=pathname+filesep()+'5_01data.sci'
+exec(filename)
+L=q*c*Cl;disp(L,"L=","L=q*c*Cl","Lift per unit span L:")
+D=q*c*Cd;disp(D,"D=","D=q*c*Cd","Drag per unit span D:")
+M=q*c*Cm*c;disp(M,"M=","M=q*c*Cm*c","Moment per unit span M:")
+printf("\Answer:\n")
+printf("\n\Lift about the quarter chord,per unit span: %f N\n\n",L)
+printf("\n\Drag about the quarter chord,per unit span: %f N\n\n",D)
+printf("\n\moment about the quarter chord,per unit span: %f N.m\n\n",M)
diff --git a/548/CH5/EX5.02/5_02.sce b/548/CH5/EX5.02/5_02.sce new file mode 100755 index 000000000..3209722ac --- /dev/null +++ b/548/CH5/EX5.02/5_02.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_02.sce')
+filename=pathname+filesep()+'5_02data.sci'
+exec(filename)
+printf("\Answer:\n")
+printf("\n\angle of attack for 700 N lift: %f degree\n\n",a)
+printf("\n\angle of attack for zero lift:: %f degree\n\n",a1)
diff --git a/548/CH5/EX5.03/5_03.sce b/548/CH5/EX5.03/5_03.sce new file mode 100755 index 000000000..c72fba469 --- /dev/null +++ b/548/CH5/EX5.03/5_03.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_03.sce')
+filename=pathname+filesep()+'5_03data.sci'
+exec(filename)
+Cp=(P1-P)/q;disp(Cp,"Cp=","Cp=(P1-P)/q","pressure coefficient Cp :")
+printf("\Answer:\n")
+printf("\n\pressure coefficient at this point of wing: %f \n\n",Cp)
\ No newline at end of file diff --git a/548/CH5/EX5.04/5_04.sce b/548/CH5/EX5.04/5_04.sce new file mode 100755 index 000000000..29758bbf1 --- /dev/null +++ b/548/CH5/EX5.04/5_04.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_04.sce')
+filename=pathname+filesep()+'5_04data.sci'
+exec(filename)
+Cp=(P1-P)/q;disp(Cp,"Cp=","Cp=(P1-P)/q","pressure coefficient Cp :")
+printf("\Answer:\n")
+printf("\n\pressure coefficient : %f \n\n",Cp)
\ No newline at end of file diff --git a/548/CH5/EX5.05/5_05.sce b/548/CH5/EX5.05/5_05.sce new file mode 100755 index 000000000..fda942924 --- /dev/null +++ b/548/CH5/EX5.05/5_05.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_05.sce')
+filename=pathname+filesep()+'5_05data.sci'
+exec(filename)
+Cp=Cpo/(sqrt(1-M^2));disp(Cp,"Cp=","Cp=Cpo/(sqrt(1-M^2))","pressure coefficient Cp :")
+printf("\Answer:\n")
+printf("\n\pressure coefficient : %f \n\n",Cp)
\ No newline at end of file diff --git a/548/CH5/EX5.06/5_06.sce b/548/CH5/EX5.06/5_06.sce new file mode 100755 index 000000000..628c60be9 --- /dev/null +++ b/548/CH5/EX5.06/5_06.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_06.sce')
+filename=pathname+filesep()+'5_06data.sci'
+exec(filename)
+P1=(q*Cp)+P;disp(P1,"P1=","P1=q*Cp+p","pressure at this point P1:")
+printf("\Answer:\n")
+printf("\n\pressure at this point : %f N/m^2\n\n",P1)
\ No newline at end of file diff --git a/548/CH5/EX5.07/5_07.sce b/548/CH5/EX5.07/5_07.sce new file mode 100755 index 000000000..aa4217a34 --- /dev/null +++ b/548/CH5/EX5.07/5_07.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('5_07.sce')
+filename=pathname+filesep()+'5_07data.sci'
+exec(filename)
+V2=V*((Cp1-Cp2)+(V1/V)^2)^0.5;
+disp(V2,"V2=","V2=V*((Cp1-Cp2)+(V1/V)^2)^0.5","velocity at point 2 V2:")
+printf("\Answer:\n")
+printf("\n\Velocity at point 2: %f m/s\n\n",V2)
\ No newline at end of file diff --git a/548/CH5/EX5.08/5_08.sce b/548/CH5/EX5.08/5_08.sce new file mode 100755 index 000000000..d67f76e2d --- /dev/null +++ b/548/CH5/EX5.08/5_08.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_08.sce')
+filename=pathname+filesep()+'5_08data.sci'
+exec(filename)
+Cn=integrate('1-0.95*y','y',0,1.0)-integrate('1-300*y^2 ','y',0,0.1)-integrate('-2.2277+2.2277*y','y',0.1,1.0)
+printf("\Answer:\n")
+printf("\n\Normal force coefficient : %f \n\n",Cn)
diff --git a/548/CH5/EX5.09/5_09.sce b/548/CH5/EX5.09/5_09.sce new file mode 100755 index 000000000..e2ed1cc69 --- /dev/null +++ b/548/CH5/EX5.09/5_09.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_09.sce')
+filename=pathname+filesep()+'5_09data.sci'
+exec(filename)
+Cl=Co/(sqrt(1-M^2));disp(Cl,"Cl=","Cl=Co/(sqrt(1-M^2))","Lift coefficient Cl :")
+printf("\Answer:\n")
+printf("\n\Lift coefficient at Mach 0.7: %f \n\n",Cl)
\ No newline at end of file diff --git a/548/CH5/EX5.10/5_10.JPG b/548/CH5/EX5.10/5_10.JPG Binary files differnew file mode 100755 index 000000000..c7b55ca9c --- /dev/null +++ b/548/CH5/EX5.10/5_10.JPG diff --git a/548/CH5/EX5.10/5_10.sce b/548/CH5/EX5.10/5_10.sce new file mode 100755 index 000000000..285a6a71c --- /dev/null +++ b/548/CH5/EX5.10/5_10.sce @@ -0,0 +1,15 @@ +pathname=get_absolute_file_path('5_10.sce')
+filename=pathname+filesep()+'5_10_data.sci'
+exec(filename)
+clf();
+i = 1;
+while(i<=length(M))
+ Cpcr(i)=(2/(y*M(i)^2))*[[(2+(y-1)*M(i)^2)/(y+1)]^(y/(y-1))-1]
+ Cpmin(i)=Cpomin/sqrt(1-M(i)^2);
+ i = i+1;
+end
+xlabel("Mach Number");
+ylabel("Cp");
+plot2d(M,Cpcr,2);
+plot2d(M,Cpmin);
+disp("The intersection point of both the graphs i.e approx 0.74 is the critical Mach no of the NACA-0012 airfoil.")
diff --git a/548/CH5/EX5.11/5_11.sce b/548/CH5/EX5.11/5_11.sce new file mode 100755 index 000000000..1bea26bfe --- /dev/null +++ b/548/CH5/EX5.11/5_11.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('5_11.sce')
+filename=pathname+filesep()+'5_11_data.sci'
+exec(filename)
+L=q*c*Cl;disp(L,"L=","L=q*c*Cl","lift per unit span for mach 3 :")
+Dw=q*c*Cd;disp(Dw,"Dw=","Dw=q*c*Cd","Wave drag per unit span for mach 3 :")
+L1=q1*c*Cl1;disp(L1,"L1=","L1=q1*c*Cl1","lift per unit span for mach 2:")
+Dw1=q1*c*Cd1;disp(Dw1,"Dw1=","Dw1=q1*c*Cd1","Wave drag per unit span for mach 2 :")
+
diff --git a/548/CH5/EX5.12/5_12.sce b/548/CH5/EX5.12/5_12.sce new file mode 100755 index 000000000..7cefdef1e --- /dev/null +++ b/548/CH5/EX5.12/5_12.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('5_12.sce')
+filename=pathname+filesep()+'5_12_data.sci'
+exec(filename)
+a=L*(M^2-1)^0.5/(4*q*S);
+disp(a,"a=","a=L*(M^2-1)^0.5/(4*q*S)","angle of attack at sea level:")
+a1=L*(M^2-1)^0.5/(4*q1*S);
+disp(a1,"a1=","a1=L*(M^2-1)^0.5/(4*q1*S)","angle of attack at 10 Km:")
+printf("\Answer:\n")
+printf("\n\angle of attack at sea level: %f degree\n\n",a*180/%pi)
+printf("\n\angle of attack at 10 Km: %f degree\n\n",a1*180/%pi)
\ No newline at end of file diff --git a/548/CH5/EX5.13/5_13.sce b/548/CH5/EX5.13/5_13.sce new file mode 100755 index 000000000..1786eae93 --- /dev/null +++ b/548/CH5/EX5.13/5_13.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('5_13.sce')
+filename=pathname+filesep()+'5_13data.sci'
+exec(filename)
+L=q*S*4*a/sqrt(M^2-1);
+disp(L,"L=","L=q*S*4*a/sqrt(M^2-1)","Lift exerted on airplane L:")
+printf("\Answer:\n")
+printf("\n\Lift exerted on airplane: %f N\n\n",L)
\ No newline at end of file diff --git a/548/CH5/EX5.14/5_14.sce b/548/CH5/EX5.14/5_14.sce new file mode 100755 index 000000000..46c7ea514 --- /dev/null +++ b/548/CH5/EX5.14/5_14.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('5_14.sce')
+filename=pathname+filesep()+'5_14data.sci'
+exec(filename)
+Cl=L/(q*S);
+disp(Cl,"Cl=","Cl=L/(q*S)","Lift coefficient Cl:")
+printf("\Answer:\n")
+printf("\n\Lift coefficient: %f \n\n",Cl)
\ No newline at end of file diff --git a/548/CH5/EX5.15/5_15.sce b/548/CH5/EX5.15/5_15.sce new file mode 100755 index 000000000..210c2b446 --- /dev/null +++ b/548/CH5/EX5.15/5_15.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('5_15.sce')
+filename=pathname+filesep()+'5_15data.sci'
+exec(filename)
+Cdi=Cl^2/(%pi*e*AR);disp(Cdi,"Cdi=","Cdi=Cl^2/(%pi*e*AR)","induced drag coefficient Cdi:")
+Di=q*S*Cdi;disp(Di,"Di=","Di=q*S*Cdi","induced drag Di:")
+printf("\Answer:\n")
+printf("\n\induced drag coefficient: %f \n\n",Cdi)
+printf("\n\induced drag: %f N\n\n",Di)
\ No newline at end of file diff --git a/548/CH5/EX5.16/5_16.sce b/548/CH5/EX5.16/5_16.sce new file mode 100755 index 000000000..23062367e --- /dev/null +++ b/548/CH5/EX5.16/5_16.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_16.sce')
+filename=pathname+filesep()+'5_16data.sci'
+exec(filename)
+Dt=(Cd+Cdi)*S*(D*V^2/2);disp(Dt,"Dt=","Dt=(Cd+Cdi)*S*q","total drag Di:")
+printf("\Answer:\n")
+printf("\n\Totl drag: %f N\n\n",Dt)
\ No newline at end of file diff --git a/548/CH5/EX5.17/5_17.sce b/548/CH5/EX5.17/5_17.sce new file mode 100755 index 000000000..aebe84a61 --- /dev/null +++ b/548/CH5/EX5.17/5_17.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('5_17.sce')
+filename=pathname+filesep()+'5_17data.sci'
+exec(filename)
+Cl=a1*(a-a2);disp(Cl,"Cl=","Cl=a1(a-a2)","lift coefficient Cl:")
+Cd=cd+Cl^2/(%pi*e*AR);disp(Cd,"Cd=","Cd=cd+Cl^2/(%pi*e*AR)","total drag coefficient Cd=:")
+printf("\Answer:\n")
+printf("\n\Lift coefficient: %f \n\n",Cl)
+printf("\n\Totl drag coefficient: %f \n\n",Cd)
\ No newline at end of file diff --git a/548/CH5/EX5.18/5_18.sce b/548/CH5/EX5.18/5_18.sce new file mode 100755 index 000000000..e8f065a60 --- /dev/null +++ b/548/CH5/EX5.18/5_18.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('5_18.sce')
+filename=pathname+filesep()+'5_18data.sci'
+exec(filename)
+Di=q*S*Cdi;disp(Di,"Di=","Di=q*S*Cdi","induced drag on one wing Di:")
+printf("\Answer:\n")
+printf("\n\Induced drag exerted on both the wings: %f N\n\n",2*Di)
diff --git a/548/CH5/EX5.19/5_19.sce b/548/CH5/EX5.19/5_19.sce new file mode 100755 index 000000000..e07be4064 --- /dev/null +++ b/548/CH5/EX5.19/5_19.sce @@ -0,0 +1,4 @@ +pathname=get_absolute_file_path('5_19.sce')
+filename=pathname+filesep()+'5_19data.sci'
+exec(filename)
+disp("comparing the results of part a and b we can see the high-aspect ratio wing experiences a 26% higher increase in Cl than the low-aspect ratio wing.")
\ No newline at end of file diff --git a/548/CH5/EX5.20/5_20.sce b/548/CH5/EX5.20/5_20.sce new file mode 100755 index 000000000..5707adcfd --- /dev/null +++ b/548/CH5/EX5.20/5_20.sce @@ -0,0 +1,9 @@ +pathname=get_absolute_file_path('5_20.sce')
+filename=pathname+filesep()+'5_20data.sci'
+exec(filename)
+V1=sqrt(2*Wt/(D*S*Clm));disp(V1,"V1=","V1=sqrt(2*Wt/(D*S*Clm))","stalling speed for full fuel tank V1:")
+V2=sqrt(2*Wf/(D*S*Clm));disp(V2,"V2=","V2=sqrt(2*Wf/(D*S*Clm))","stalling speed for empty fuel tank V1:")
+printf("\Answer:\n")
+printf("\n\stalling speed for full fuel tank : %f m/s\n\n",V1)
+printf("\n\stalling speed for empty fuel tank : %f m/s\n\n",V2)
+
diff --git a/548/CH5/EX5.21/5_21.sce b/548/CH5/EX5.21/5_21.sce new file mode 100755 index 000000000..c68868168 --- /dev/null +++ b/548/CH5/EX5.21/5_21.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('5_21.sce')
+filename=pathname+filesep()+'5_21data.sci'
+exec(filename)
+V=sqrt(2*Wt/(D*S*Clm));disp(V,"V=","V=sqrt(2*Wt/(D*S*Clm))","stalling speed for Boeing 727 V:")
+printf("\Answer:\n")
+printf("\n\stalling speed for full fuel tank : %f m/s\n\n",V)
+disp("stalling speed for lockhead F-104 is a much higher value than the Boeing 727.","comparison with stalling speed for full fuel tank of example 5.20:")
\ No newline at end of file diff --git a/548/CH6/EX6.1.a/6_1a.JPG b/548/CH6/EX6.1.a/6_1a.JPG Binary files differnew file mode 100755 index 000000000..1bfa69781 --- /dev/null +++ b/548/CH6/EX6.1.a/6_1a.JPG diff --git a/548/CH6/EX6.1.a/6_1a.sce b/548/CH6/EX6.1.a/6_1a.sce new file mode 100755 index 000000000..b2159f4a7 --- /dev/null +++ b/548/CH6/EX6.1.a/6_1a.sce @@ -0,0 +1,16 @@ +pathname=get_absolute_file_path('6_1a.sce')
+filename=pathname+filesep()+'6_1a_data.sci'
+exec(filename)
+clf();
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Thrust (kN)");
+plot2d(V,Thrust,3);
diff --git a/548/CH6/EX6.1.b/6_1b.JPG b/548/CH6/EX6.1.b/6_1b.JPG Binary files differnew file mode 100755 index 000000000..86749bd67 --- /dev/null +++ b/548/CH6/EX6.1.b/6_1b.JPG diff --git a/548/CH6/EX6.1.b/6_1b.sce b/548/CH6/EX6.1.b/6_1b.sce new file mode 100755 index 000000000..3fd773e19 --- /dev/null +++ b/548/CH6/EX6.1.b/6_1b.sce @@ -0,0 +1,18 @@ +pathname=get_absolute_file_path('6_1b.sce')
+filename=pathname+filesep()+'6_1b_data.sci'
+exec(filename)
+clf();
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Thrust (kN)");
+plot2d(V,Thrust,3);
+
+
diff --git a/548/CH6/EX6.12/6_12.sce b/548/CH6/EX6.12/6_12.sce new file mode 100755 index 000000000..ebb6e211c --- /dev/null +++ b/548/CH6/EX6.12/6_12.sce @@ -0,0 +1,28 @@ +pathname=get_absolute_file_path('6_12.sce')
+filename=pathname+filesep()+'6_12data.sci'
+exec(filename)
+clf();
+V=linspace(20,120,500);
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*Wo/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Cl1_Cd(i)=Cl(i)^1.5/Cd(i)
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+plot2d(V,Cl_Cd,3);
+plot2d(V,Cl1_Cd,4);
+//from graph we can see:
+Cl_Cdmax=13.62;//maximum Cl/Cd
+Cl1_Cdmax=12.81;//maximum Cl^1.5/Cd
+R=(n/c)*Cl_Cdmax*log(Wo/W1)
+disp(R,"R=","Range R=(n/c)*(Cl/Cd)*log(Wo/W1)")
+E=(n/c)*Cl1_Cdmax*sqrt(2*D*S)*[1/sqrt(W1)-1/sqrt(Wo)]
+disp(E,"E=","Endurance E=(n/c)*(Cl^1.5/Cd)*sqrt(2*D*S)*[1/sqrt(W1)-1/sqrt(Wo)]")
+printf("\Answer:\n")
+printf("\n\Maximum range of CP-1: %f m\n\n",R)
+printf("\n\Maximum Endurance of CP-1: %f s\n\n",E)
+
diff --git a/548/CH6/EX6.13/6_13.sce b/548/CH6/EX6.13/6_13.sce new file mode 100755 index 000000000..c1f157ef5 --- /dev/null +++ b/548/CH6/EX6.13/6_13.sce @@ -0,0 +1,28 @@ +pathname=get_absolute_file_path('6_13.sce')
+filename=pathname+filesep()+'6_13data.sci'
+exec(filename)
+clf();
+V=linspace(20,400,500);
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*Wo/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Cl1_Cd(i)=Cl(i)^0.5/Cd(i)
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+plot2d(V,Cl_Cd,3);
+plot2d(V,Cl1_Cd,4);
+//from graph we can see:
+Cl_Cdmax=16.9;//maximum Cl/Cd
+Cl1_Cdmax=23.4;//maximum Cl^0.5/Cd
+R=[sqrt(Wo)-sqrt(W1)]*Cl1_Cdmax*2*(sqrt(2/(D*S))/c);
+disp(R,"R=","Range R=[sqrt(Wo)-sqrt(W1)]*Cl^.5/Cd*2*(sqrt(2/(D*S))/c)")
+E=(Cl_Cdmax*log(Wo/W1))/c;
+disp(E,"E=","Endurance E=(Cl_Cdmax*log(Wo/W1))/c")
+printf("\Answer:\n")
+printf("\n\Maximum range of CJ-1: %f m\n\n",R)
+printf("\n\Maximum Endurance of CJ-1: %f s\n\n",E)
+
diff --git a/548/CH6/EX6.14/6_14.sce b/548/CH6/EX6.14/6_14.sce new file mode 100755 index 000000000..47bea784e --- /dev/null +++ b/548/CH6/EX6.14/6_14.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_14.sce')
+filename=pathname+filesep()+'6_14data.sci'
+exec(filename)
+Cl_Cdmax=sqrt(Cdo*%pi*e*AR)/(2*Cdo);
+disp(Cl_Cdmax,"(Cl/Cd)max=","(Cl/Cd)max=sqrt(Cdo*%pi*e*AR)/(2*Cdo)")
+Cl_Cd1max=(3*Cdo*%pi*e*AR)^(3/4)/(4*Cdo);
+disp(Cl_Cd1max,"((Cl/Cd)^1.5)max=","((Cl/Cd)^1.5)max=(3*Cdo*%pi*e*AR)^(3/4)/(4*Cdo)")
\ No newline at end of file diff --git a/548/CH6/EX6.15/6_15.sce b/548/CH6/EX6.15/6_15.sce new file mode 100755 index 000000000..85d71971a --- /dev/null +++ b/548/CH6/EX6.15/6_15.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_15.sce')
+filename=pathname+filesep()+'6_15data.sci'
+exec(filename)
+Cl_Cdmax=sqrt(Cdo*%pi*e*AR)/(2*Cdo);
+disp(Cl_Cdmax,"(Cl/Cd)max=","(Cl/Cd)max=sqrt(Cdo*%pi*e*AR)/(2*Cdo)")
+Cl_Cd1max=((1/3)*Cdo*%pi*e*AR)^(1/4)/(4*Cdo/3);
+disp(Cl_Cd1max,"(Cl^0.5/Cd)max=","(Cl^0.5/Cd)max=((1/3)*Cdo*%pi*e*AR)^(1/4)/(4*Cdo/3)")
\ No newline at end of file diff --git a/548/CH6/EX6.16.b/6_16b.sce b/548/CH6/EX6.16.b/6_16b.sce new file mode 100755 index 000000000..565f7ee06 --- /dev/null +++ b/548/CH6/EX6.16.b/6_16b.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('6_16b.sce')
+filename=pathname+filesep()+'6_16b_data.sci'
+exec(filename)
+R_Cmax=(Pf*P*746/W)-0.8776*sqrt(W/(D*S*Cdo))*(1/(L_Dmax)^1.5)//(R/C)max
+printf("\Answer:\n")
+printf("\n\Maximum Rate of climd for CP-1: %f m/s\n\n",R_Cmax)
\ No newline at end of file diff --git a/548/CH6/EX6.16.c/6_16c.sce b/548/CH6/EX6.16.c/6_16c.sce new file mode 100755 index 000000000..27c7c91c5 --- /dev/null +++ b/548/CH6/EX6.16.c/6_16c.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_16c.sce')
+filename=pathname+filesep()+'6_16c_data.sci'
+exec(filename)
+A=2*Tf/W;B=W/S;C=1/L_Dmax^2;E=sqrt(A^2-C)
+Vmax=sqrt((A*B+B*E)/(D*Cdo))
+printf("\Answer:\n")
+printf("\n\Maximum Velocity for CJ-1: %f m/s\n\n",Vmax)
\ No newline at end of file diff --git a/548/CH6/EX6.16.d/6_16d.sce b/548/CH6/EX6.16.d/6_16d.sce new file mode 100755 index 000000000..6621cb4d7 --- /dev/null +++ b/548/CH6/EX6.16.d/6_16d.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_16d.sce')
+filename=pathname+filesep()+'6_16d_data.sci'
+exec(filename)
+Z=1+sqrt(1+(3/((L_Dmax)^2*(2*Tf/W)^2)))
+R_Cmax=sqrt(W*Z/(3*D*Cdo*S))*(2*Tf/W)^1.5*[1-(Z/6)-(1.5/(Z*(2*Tf/W)^2*(L_Dmax)^2))]
+printf("\Answer:\n")
+printf("\n\Maximum Rate of Climb for CJ-1: %f m/s\n\n",R_Cmax)
\ No newline at end of file diff --git a/548/CH6/EX6.17/6_17.sce b/548/CH6/EX6.17/6_17.sce new file mode 100755 index 000000000..5d3c8dd1c --- /dev/null +++ b/548/CH6/EX6.17/6_17.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_17.sce')
+filename=pathname+filesep()+'6_17data.sci'
+exec(filename)
+Sl=1.44*W^2/(g*D*S*Cl*[T-(Dr+Ur*(W-L))]);;disp(Sl,"Sl=","Sl=1.44*W^2/(g*D*S*Cl*[T-(Dr+Ur*(W-L))])","Liftoff distance Sl:")
+printf("\Answer:\n")
+printf("\n\Liftoff distance for the CJ-1 at se level: %f m\n\n",Sl)
+
diff --git a/548/CH6/EX6.18/6_18.sce b/548/CH6/EX6.18/6_18.sce new file mode 100755 index 000000000..b865db2e6 --- /dev/null +++ b/548/CH6/EX6.18/6_18.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('6_18.sce')
+filename=pathname+filesep()+'6_18data.sci'
+exec(filename)
+Sl=(Vt^2*W)/(2*g*(Dr+Ur*W));disp(Sl,"Sl=","Sl=(Vt^2*W)/(2*g*(Dr+Ur*W))","landing ground roll distance Sl:")
+printf("\Answer:\n")
+printf("\n\Landing ground roll distance at sea level: %f m\n\n",Sl)
+
diff --git a/548/CH6/EX6.19.a/6_19a.sce b/548/CH6/EX6.19.a/6_19a.sce new file mode 100755 index 000000000..8f05e737e --- /dev/null +++ b/548/CH6/EX6.19.a/6_19a.sce @@ -0,0 +1,9 @@ +pathname=get_absolute_file_path('6_19a.sce')
+filename=pathname+filesep()+'6_19data.sci'
+exec(filename)
+A=D*S*Cdo/2;
+B=2*Wo^2/(D*S*%pi*e*AR);
+V=poly(0,'V');
+p=Pa*V-A*V^4-B
+disp(roots(p),"Roots of Polynomial p:",p,"p=","Polynomial p:")
+disp("As we can see the maximum positive root is 81.01 (approx), which is the maximum velocity at sea level of the UAV.")
diff --git a/548/CH6/EX6.19.b/6_19b.sce b/548/CH6/EX6.19.b/6_19b.sce new file mode 100755 index 000000000..5ca122136 --- /dev/null +++ b/548/CH6/EX6.19.b/6_19b.sce @@ -0,0 +1,10 @@ +pathname=get_absolute_file_path('6_19b.sce')
+filename=pathname+filesep()+'6_19data.sci'
+exec(filename)
+disp("(R/C)max=(P/W)max-0.8776*sqrt(W/(S*D*Cdo))*(Cd/Cl)^1.5")
+A=Pa/Wo;
+Cd_Cl=2*Cdo/sqrt(Cdo*%pi*e*AR);//ratio , Cd/Cl
+B=0.8776*sqrt(Wo/(S*D*Cdo))*(Cd_Cl)^1.5;
+R_Cmax=A-B;//maximum rate of climb
+printf("\Answer:\n")
+printf("\n\maximum rate of climb at sea level: %f m/s\n\n",R_Cmax)
\ No newline at end of file diff --git a/548/CH6/EX6.19.c/6_19c.sce b/548/CH6/EX6.19.c/6_19c.sce new file mode 100755 index 000000000..33bd6e735 --- /dev/null +++ b/548/CH6/EX6.19.c/6_19c.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('6_19c.sce')
+filename=pathname+filesep()+'6_19data.sci'
+exec(filename)
+Cl_Cd=sqrt(Cdo*%pi*e*AR)/(2*Cdo);//ratio(Cl/Cd)
+disp(Cl_Cd)
+R=(n/c)*Cl_Cd*log(Wo/(W-W1))*0.62137*10^-3 ;//range in miles
+printf("\Answer:\n")
+printf("\n\maximum range: %f miles\n\n",R)
\ No newline at end of file diff --git a/548/CH6/EX6.19.d/6_19d.sce b/548/CH6/EX6.19.d/6_19d.sce new file mode 100755 index 000000000..7dea11332 --- /dev/null +++ b/548/CH6/EX6.19.d/6_19d.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('6_19d.sce')
+filename=pathname+filesep()+'6_19data.sci'
+exec(filename)
+E=(n/(4*c*Cdo))*(3*Cdo*%pi*e*AR)^(3/4)*sqrt(2*D*S)*[1/sqrt(W-W1)-1/sqrt(Wo)]
+printf("\Answer:\n")
+printf("\n\Maximum Endurance at sea level: %f s\n\n",E)
\ No newline at end of file diff --git a/548/CH6/EX6.2/602.JPG b/548/CH6/EX6.2/602.JPG Binary files differnew file mode 100755 index 000000000..cdf549d2f --- /dev/null +++ b/548/CH6/EX6.2/602.JPG diff --git a/548/CH6/EX6.2/602.sce b/548/CH6/EX6.2/602.sce new file mode 100755 index 000000000..0cf6c4dc2 --- /dev/null +++ b/548/CH6/EX6.2/602.sce @@ -0,0 +1,23 @@ +pathname=get_absolute_file_path('602.sce')
+filename=pathname+filesep()+'602data.sci'
+exec(filename)
+clf();
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ Tf(i)=2*16245/1000;
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Thrust (kN)");
+plot2d(V,Thrust,3);
+plot2d(V,Tf,4);
+disp("As Thrust required equals Thrust provided by two turbofan at Velocity 297 m/s approx(intersection point of both graphs.)so it will be Vmax")
+Vmax=297;
+printf("\Answer:\n")
+printf("\n\maximum velocity: %f m/s\n\n",Vmax)
+
diff --git a/548/CH6/EX6.20/6_20.sce b/548/CH6/EX6.20/6_20.sce new file mode 100755 index 000000000..6429a643c --- /dev/null +++ b/548/CH6/EX6.20/6_20.sce @@ -0,0 +1,11 @@ +pathname=get_absolute_file_path('6.20.sce')
+filename=pathname+filesep()+'6.20data.sci'
+exec(filename)
+R1_R2=sqrt((n2^2-1)/(n1^2-1));//ratio(R1/R2)
+disp(R1_R2,"ratio of turn radius :R1/R2=sqrt((n2^2-1)/(n1^2-1))")
+w1_w2=sqrt((n1^2-1)/(n2^2-1));//ratio(w1/w2)
+disp(w1_w2,"ratio of turn rate :w1/w2=sqrt((n1^2-1)/(n2^2-1))")
+printf("\Answer:\n")
+printf("\n\Ratio of turn radius: %f \n\n",R1_R2)
+printf("\n\Ratio of turn rate: %f m/s\n\n",w1_w2)
+
diff --git a/548/CH6/EX6.3.a/6_3a.JPG b/548/CH6/EX6.3.a/6_3a.JPG Binary files differnew file mode 100755 index 000000000..ac8a12118 --- /dev/null +++ b/548/CH6/EX6.3.a/6_3a.JPG diff --git a/548/CH6/EX6.3.a/6_3a.sce b/548/CH6/EX6.3.a/6_3a.sce new file mode 100755 index 000000000..75c8ab663 --- /dev/null +++ b/548/CH6/EX6.3.a/6_3a.sce @@ -0,0 +1,18 @@ +pathname=get_absolute_file_path('6_3a.sce')
+filename=pathname+filesep()+'6_3a_data.sci'
+exec(filename)
+clf();
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ Power(i)=Thrust(i)*V(i);
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Power (KN-m/s)");
+plot2d(V,Power,5);
+
diff --git a/548/CH6/EX6.3.b/6_3b.JPG b/548/CH6/EX6.3.b/6_3b.JPG Binary files differnew file mode 100755 index 000000000..b6aae5e83 --- /dev/null +++ b/548/CH6/EX6.3.b/6_3b.JPG diff --git a/548/CH6/EX6.3.b/6_3b.sce b/548/CH6/EX6.3.b/6_3b.sce new file mode 100755 index 000000000..9396ce670 --- /dev/null +++ b/548/CH6/EX6.3.b/6_3b.sce @@ -0,0 +1,17 @@ +pathname=get_absolute_file_path('6_3b.sce')
+filename=pathname+filesep()+'6_3b_data.sci'
+exec(filename)
+clf();
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ Power(i)=Thrust(i)*V(i)
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Power (KN-m/s)");
+plot2d(V,Power,5);
diff --git a/548/CH6/EX6.4.a/6_4a.JPG b/548/CH6/EX6.4.a/6_4a.JPG Binary files differnew file mode 100755 index 000000000..7cfdbea8e --- /dev/null +++ b/548/CH6/EX6.4.a/6_4a.JPG diff --git a/548/CH6/EX6.4.a/6_4a.sce b/548/CH6/EX6.4.a/6_4a.sce new file mode 100755 index 000000000..9830fdde0 --- /dev/null +++ b/548/CH6/EX6.4.a/6_4a.sce @@ -0,0 +1,22 @@ +pathname=get_absolute_file_path('6_4a.sce')
+filename=pathname+filesep()+'6_4a_data.sci'
+exec(filename)
+clf();
+V=linspace(20,300,500);
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ Power(i)=Thrust(i)*V(i);
+ Pa(i)=P*Pf*746/1000;
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Power (KN-m/s)");
+plot2d(V,Power,4);
+plot2d(V,Pa,5);
+disp("the intersection of both graph shows maximum velocity of CP-1 at sea level which is arround 81m/s.")
+
diff --git a/548/CH6/EX6.4.b/6_4b.JPG b/548/CH6/EX6.4.b/6_4b.JPG Binary files differnew file mode 100755 index 000000000..6e58d4acd --- /dev/null +++ b/548/CH6/EX6.4.b/6_4b.JPG diff --git a/548/CH6/EX6.4.b/6_4b.sce b/548/CH6/EX6.4.b/6_4b.sce new file mode 100755 index 000000000..2a5e2219e --- /dev/null +++ b/548/CH6/EX6.4.b/6_4b.sce @@ -0,0 +1,21 @@ +pathname=get_absolute_file_path('6_4b.sce')
+filename=pathname+filesep()+'6_4b_data.sci'
+exec(filename)
+clf();
+V=linspace(40,300,500);
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;//unit KN
+ Power(i)=Thrust(i)*V(i)//unit KN-m/s
+ Pa(i)=D*Tf*V(i)/(Do*1000);//power(KN-m/s) at height 6706.5 m corresponding to velocity
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Power (KN-m/s)");
+plot2d(V,Power,4);
+plot2d(V,Pa,5);
+disp("As we can see the higher intersection point of both curve is arround 294m/s(approx),which is the maximum velocity for CJ-1 at 6705.6 meter.")
\ No newline at end of file diff --git a/548/CH6/EX6.5/6_05.JPG b/548/CH6/EX6.5/6_05.JPG Binary files differnew file mode 100755 index 000000000..387a87878 --- /dev/null +++ b/548/CH6/EX6.5/6_05.JPG diff --git a/548/CH6/EX6.5/6_05.sce b/548/CH6/EX6.5/6_05.sce new file mode 100755 index 000000000..65adb2812 --- /dev/null +++ b/548/CH6/EX6.5/6_05.sce @@ -0,0 +1,22 @@ +pathname=get_absolute_file_path('6_05.sce')
+filename=pathname+filesep()+'6_05data.sci'
+exec(filename)
+clf();
+V=linspace(40,300,500);
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;Vo=0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Vo(i)=V(i)*(D/Do)^0.5;//corresponding velocity points at sea level
+ Thrust(i) = W/Cl_Cd(i)/1000;//unit KN
+ Power(i)=Thrust(i)*Vo(i)//unit KN-m/s
+ Pa(i)=D*Tf*Vo(i)/(Do*1000);//power(KN-m/s) at height 6706.5 m corresponding to velocity
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Power (KN-m/s)");
+plot2d(Vo,Power,4);
+plot2d(Vo,Pa,5)
+printf("\nmaximum velocity for CJ-1 approx 210m/s(as seen from graph)")
\ No newline at end of file diff --git a/548/CH6/EX6.6/6_06.JPG b/548/CH6/EX6.6/6_06.JPG Binary files differnew file mode 100755 index 000000000..82610b983 --- /dev/null +++ b/548/CH6/EX6.6/6_06.JPG diff --git a/548/CH6/EX6.6/6_06.sce b/548/CH6/EX6.6/6_06.sce new file mode 100755 index 000000000..65f9769bb --- /dev/null +++ b/548/CH6/EX6.6/6_06.sce @@ -0,0 +1,20 @@ +pathname=get_absolute_file_path('6_06.sce')
+filename=pathname+filesep()+'6_06data.sci'
+exec(filename)
+clf();
+
+i = 1;
+Cl = 0;Cd = 0;Cl_Cd =0;Thrust = 0;
+while(i<=length(V))
+ Cl(i) = 2*W/(D*S*V(i)^2);
+ Cd(i) = Cdo + Cl(i)^2/(%pi*e*AR);
+ Cl_Cd(i) = Cl(i)/Cd(i);
+ Thrust(i) = W/Cl_Cd(i)/1000;
+ Power(i)=Thrust(i)*V(i);
+ R_C(i)=(Pa-Power(i))*1000*60/W;//rate of climb(R/C in meter per minute)
+ i = i+1;
+end
+xlabel("Velocity (m/s)");
+ylabel("Rate of climb(m/min) for CP-1");
+plot2d(V,R_C,4);
+
diff --git a/548/CH6/EX6.7/6_07.sce b/548/CH6/EX6.7/6_07.sce new file mode 100755 index 000000000..eec83c4b7 --- /dev/null +++ b/548/CH6/EX6.7/6_07.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('6_07.sce')
+filename=pathname+filesep()+'6_07data.sci'
+exec(filename)
+a=atand(1/L_D);disp(a,"a=","tan(a)=1/(L/D)","minimum glide angle a:")
+R=H*L_D;disp(R,"R=","R=H*L/D","maximum range along ground :")
+printf("\Answer:\n")
+printf("\minimum glide angle: %f \n",a)
+printf("\n\maximum range covered along ground: %f m\n\n",R)
\ No newline at end of file diff --git a/548/CH6/EX6.8/6_08.sce b/548/CH6/EX6.8/6_08.sce new file mode 100755 index 000000000..38d308dda --- /dev/null +++ b/548/CH6/EX6.8/6_08.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('6_08.sce')
+filename=pathname+filesep()+'6_08data.sci'
+exec(filename)
+a=atand(1/L_D);disp(a,"a=","tan(a)=1/(L/D)","minimum glide angle a:")
+R=H*L_D;disp(R,"R=","R=H*L/D","maximum range along ground :")
+printf("\Answer:\n")
+printf("\minimum glide angle: %f degree\n",a)
+printf("\n\maximum range covered along ground: %f m\n\n",R)
\ No newline at end of file diff --git a/548/CH6/EX6.9/6_09.sce b/548/CH6/EX6.9/6_09.sce new file mode 100755 index 000000000..b5388a5ed --- /dev/null +++ b/548/CH6/EX6.9/6_09.sce @@ -0,0 +1,8 @@ +pathname=get_absolute_file_path('6_09.sce')
+filename=pathname+filesep()+'6_09data.sci'
+exec(filename)
+V1=sqrt(2*Wl*cos(a)/(D1*Cl));disp(V1,"V1=","V1=sqrt(2*Wl*cos(a)/(D1*Cl))","For altitude 3048 meter:")
+V2=sqrt(2*Wl*cos(a)/(D2*Cl));disp(V2,"V2=","V2=sqrt(2*Wl*cos(a)/(D2*Cl))","For altitude 609.6 meter:")
+printf("\Answer:\n")
+printf("\Velocity at equilibrium glide angle at 3048 m: %f m/s\n",V1)
+printf("\n\Velocity at equilibrium glide angle at 609.6 m: %f m/s\n\n",V2)
\ No newline at end of file diff --git a/548/CH7/EX7.1/7_01.sce b/548/CH7/EX7.1/7_01.sce new file mode 100755 index 000000000..373dc37e3 --- /dev/null +++ b/548/CH7/EX7.1/7_01.sce @@ -0,0 +1,7 @@ +funcprot(0);
+function[y] = f(x,y)
+ z = poly(0,'z');
+ y = x^2+y^2+ z^2;
+endfunction
+ans= derivat(f(1,1)); // finding derivative with respect to z at some point x,y;
+disp(ans,"derivative of x^2+y^2+ z^2 with respect to z:");
diff --git a/548/CH7/EX7.2/7_02.sce b/548/CH7/EX7.2/7_02.sce new file mode 100755 index 000000000..a0ed36ed8 --- /dev/null +++ b/548/CH7/EX7.2/7_02.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('7_02.sce')
+filename=pathname+filesep()+'7_02data.sci'
+exec(filename)
+Cmcg=Cmac+Clwb*(dh);disp(Cmcg,"Cmcg","Cmcg=Cmac+Clwb(dh)","moment coefficient about center of gravity Cmcg")
+printf("\Answer:\n")
+printf("\n\moment coefficient about center of gravity : %f \n\n",Cmcg)
diff --git a/548/CH7/EX7.3/7_03.sce b/548/CH7/EX7.3/7_03.sce new file mode 100755 index 000000000..042da971e --- /dev/null +++ b/548/CH7/EX7.3/7_03.sce @@ -0,0 +1,13 @@ +pathname=get_absolute_file_path('7_03.sce')
+filename=pathname+filesep()+'7_03data.sci'
+exec(filename)
+A=[1,Awb*ab2;1,Awb*ab3];
+B=[1,1];//coefficient of moment coefficient about aerodynamic center
+C=[Awb*ab2,Awb*ab3];//coefficient of h-hac
+D=[-0.01,0.05];
+dh=det([B;D])/det(A);//difference between location of aerodynamic center and center of gravity
+hac=h-dh;
+Cmac=det([D;C])/det(A)//moment coefficient about aerodynamic center
+printf("\Answer:\n")
+printf("\n\Location of aerodynamic center: %f\n\n",hac)
+printf("\n\moment coefficient about aerodynamic center of wing-body : %f\n\n",Cmac)
\ No newline at end of file diff --git a/548/CH7/EX7.4/7_04.sce b/548/CH7/EX7.4/7_04.sce new file mode 100755 index 000000000..ee3c3b0e2 --- /dev/null +++ b/548/CH7/EX7.4/7_04.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('7_04.sce')
+filename=pathname+filesep()+'7_04data.sci'
+exec(filename)
+Cmcg=Cmac+a*a1*(dh-Vh*at*(1-de)/a)+Vh*at*(It+eo)
+disp(Cmcg,"Cmcg=","Cmcg=Cmac+a*a1*(dh-Vh*at(1-de)/a)+Vh*at*(It+eo)","moment coefficient about COG Cmcg:")
+printf("\Answer:\n")
+printf("\n\moment coefficient about center of gravity : %f \n\n",Cmcg)
diff --git a/548/CH7/EX7.5/7_05.sce b/548/CH7/EX7.5/7_05.sce new file mode 100755 index 000000000..78f540f5f --- /dev/null +++ b/548/CH7/EX7.5/7_05.sce @@ -0,0 +1,5 @@ +pathname=get_absolute_file_path('7_05.sce')
+filename=pathname+filesep()+'7_05data.sci'
+exec(filename)
+disp("->as slope (DCmg) of moment coefficient curve is negative the airplane model is statically stable.")
+disp("->as equilibrium angle of attack (Ae) falls in a reasonable range, the plane is longitudinally stable.")
\ No newline at end of file diff --git a/548/CH7/EX7.6/7_06.sce b/548/CH7/EX7.6/7_06.sce new file mode 100755 index 000000000..93a6ea3da --- /dev/null +++ b/548/CH7/EX7.6/7_06.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('7_06.sce')
+filename=pathname+filesep()+'7_06data.sci'
+exec(filename)
+Hn=Hac+Vh*at*(1-de)/a;
+disp(Hn,"Hn=","Hn=Hac+Vh*at*(1-de)/a","neutral point location Hn:")
+printf("\Answer:\n")
+printf("\n\Neutral point location : %f \n\n",Hn)
diff --git a/548/CH7/EX7.7/7_07.sce b/548/CH7/EX7.7/7_07.sce new file mode 100755 index 000000000..4cd3bc3e6 --- /dev/null +++ b/548/CH7/EX7.7/7_07.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('7_07.sce')
+filename=pathname+filesep()+'7_07data.sci'
+exec(filename)
+Sm=Hn-h;disp(Sm,"Sm=","Sm=Hn-h","static margin Sm:")
+printf("\Answer:\n")
+printf("\n\Static Margin : %f \n\n",Sm)
diff --git a/548/CH7/EX7.8/7_08.sce b/548/CH7/EX7.8/7_08.sce new file mode 100755 index 000000000..4737b94ec --- /dev/null +++ b/548/CH7/EX7.8/7_08.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('7_08.sce')
+filename=pathname+filesep()+'7_08data.sci'
+exec(filename)
+Dtrm=(Cmo+DCmcg*a1)/(Vh*DClt);
+disp(Dtrm,"Dtrm=","Dtrm=(Cmo+DCmg*a1)/(Vh*DClt)","elevator deflection angle Dtrm::")
+printf("\Answer:\n")
+printf("\n\To trim the airplane at an angle of attack of 6.5 degree the elevator must be deflected upward(negative) by : %f degree\n\n",Dtrm)
diff --git a/548/CH7/EX7.9/7_09.sce b/548/CH7/EX7.9/7_09.sce new file mode 100755 index 000000000..b84663436 --- /dev/null +++ b/548/CH7/EX7.9/7_09.sce @@ -0,0 +1,4 @@ +pathname=get_absolute_file_path('7_09.sce')
+filename=pathname+filesep()+'7_09data.sci'
+exec(filename)
+disp("for stick fixed condition neutral point is at 0.516(from example 7.6) but for stick free condition it is approx 0.448,hence moving forward and decreasing the stability")
\ No newline at end of file diff --git a/548/CH8/EX8.1/8_01.sce b/548/CH8/EX8.1/8_01.sce new file mode 100755 index 000000000..defd167a5 --- /dev/null +++ b/548/CH8/EX8.1/8_01.sce @@ -0,0 +1,9 @@ +pathname=get_absolute_file_path('8_01.sce')
+filename=pathname+filesep()+'8_01data.sci'
+exec(filename)
+h=Rb*V*cos(alpha);disp(h,"h=","h=Rb*V*cos(alpha)")
+P=h^2/K;disp(P,"P=")
+e=sqrt(1+2*(h^2/K^2)*((V^2/2)-(K/Rb)));disp(e,"e=","e=sqrt(1+2*(h^2/K^2)*((V^2/2)-(K/Rb)))")
+C=-acosd((P/Rb-1)/e);
+disp(C,"C=","C=-acosd((P/Rb-1)/e)");
+disp("equals approx 1.056*10^7/(1+0.4654*cos(theta+9.46))","P/(1+e*cos(theta-C))","From the above values we can see equation of trajectory :")
\ No newline at end of file diff --git a/548/CH8/EX8.2/8_02.sce b/548/CH8/EX8.2/8_02.sce new file mode 100755 index 000000000..ae8b12fc6 --- /dev/null +++ b/548/CH8/EX8.2/8_02.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('8_02.sce')
+filename=pathname+filesep()+'8_02data.sci'
+exec(filename)
+T2=T1*(a2/a1)^1.5;
+disp(T2,"T2=","T2=T1*(a2/a1)^1.5","period of mars T2 from keplers third law:")
+printf("\Answer:\n")
+printf("\n\Period of mars: %f days\n\n",T2)
diff --git a/548/CH8/EX8.3/8_03.sce b/548/CH8/EX8.3/8_03.sce new file mode 100755 index 000000000..ccb5a5ef4 --- /dev/null +++ b/548/CH8/EX8.3/8_03.sce @@ -0,0 +1,15 @@ +pathname=get_absolute_file_path('8_03.sce')
+filename=pathname+filesep()+'8_03data.sci'
+exec(filename)
+h=-log(D/Do)/Z;disp(h,"h=","h=-ln(D/Do)/Z","altitude of maximum decelation h:")
+Amax=Ve^2*Z*sin(theta)/(2*%e);disp(Amax,"Amax=","Amax=V^2*Z*sin(theta)/(2*%e)","value of maximum deceleration Amax")
+V=Ve*%e^(-Do/(2*B*Z*sin(theta)));disp(V,"V=","V=Ve*%e^(-Do/(2*B*Z*sin(theta)))","velocity at impact on earth surface")
+printf("\Answer:\n")
+printf("\n\altitude at which maximum deceleration occur: %f m\n\n",h)
+printf("\n\value of maximum deceleration: %f m/s^2\n\n",Amax)
+printf("\n\velocity at impact on earth surface: %f m/s\n\n",V)
+
+
+
+
+
diff --git a/548/CH9/EX9.1/9_01.sce b/548/CH9/EX9.1/9_01.sce new file mode 100755 index 000000000..9bdd8718c --- /dev/null +++ b/548/CH9/EX9.1/9_01.sce @@ -0,0 +1,17 @@ +pathname=get_absolute_file_path('9_01.sce')
+filename=pathname+filesep()+'9_01data.sci'
+exec(filename)
+x=poly(0,'x');
+P=x-10*x+9.5;
+t=roots(P);
+V2=%pi*b^2*(Stroke+t)*(10^-6)/4;disp(V2,"V2=%pi*b^2*(Stroke+t)/4");
+V3=V2/r;disp(V3,"V3=V2/r");
+V5=V2;V4=V3;
+Wcomp=(P2*V2-P3*V3)/(1-y);
+disp(Wcomp,"Wcomp=","Wcomp=P2*V2-P3*V3/(1-y);","work done in compression cycle Wcomp:")
+Wpower=(P5*V5-P4*V4)/(1-y);
+disp(Wpower,"Wpower=","Wpower=P5*V5-P4*V4/(1-y);","work done in power stroke Wpower:")
+Pa=6*n*nm*(rpm)*(Wpower-Wcomp)/120;
+disp(Pa,"Pa=n*nm*(rpm)*(Wpower-Wcomp)/120","power available Pa:")
+printf("\Answer:\n")
+printf("\n\Power available from the engine propeller combination: %f J/s \n\n",Pa)
diff --git a/548/CH9/EX9.2/9_02.sce b/548/CH9/EX9.2/9_02.sce new file mode 100755 index 000000000..c6de3996a --- /dev/null +++ b/548/CH9/EX9.2/9_02.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('9_02.sce')
+filename=pathname+filesep()+'9_02data.sci'
+exec(filename)
+Pe=Pa*120/(n*Nmech*rpm*d);
+disp(Pe,"Pe=","Pe=Pa*120/(n*Nmech*rpm*d)","mean effective pressure Pe:")
+printf("\Answer:\n")
+printf("\n\Mean effective pressure : %f N/m^2\n\n",Pe)
diff --git a/548/CH9/EX9.3/9_03.sce b/548/CH9/EX9.3/9_03.sce new file mode 100755 index 000000000..1c5a31030 --- /dev/null +++ b/548/CH9/EX9.3/9_03.sce @@ -0,0 +1,7 @@ +pathname=get_absolute_file_path('9_03.sce')
+filename=pathname+filesep()+'9_03data.sci'
+exec(filename)
+T=Mdot*(Ve-V)+(Pe-P)*Ae;
+disp(T,"T=","T=Mdot*(Ve-V)+(Pe-P)*Ae","Thrust of the turbojet T:")
+printf("\Answer:\n")
+printf("\n\Mean effective pressure : %f N\n\n",T)
diff --git a/548/CH9/EX9.4/9_04.sce b/548/CH9/EX9.4/9_04.sce new file mode 100755 index 000000000..8d0efc5db --- /dev/null +++ b/548/CH9/EX9.4/9_04.sce @@ -0,0 +1,11 @@ +pathname=get_absolute_file_path('9_04.sce')
+filename=pathname+filesep()+'9_04data.sci'
+exec(filename)
+T=Mdot*Ve;disp(T,"T=","T=Mdot*Ve","As Pe equals ambient pressure at 30 Km Thrust T:")
+Ae=Mdot/(De*Ve);disp(Ae,"Ae=","Ae=Mdot/(De*Ve)","exit area Ae:")
+Me=Ve/sqrt(y*R*Te);disp(Me,"Me=","Me=Ve/sqrt(y*R*T)","exit Mach No. Me:")
+printf("\Answer:\n")
+printf("\n\Specific impulse : %f s\n\n",Isp)
+printf("\n\Thrust: %f N\n\n",T)
+printf("\n\Area of the exit: %f m^2\n\n",Ae)
+printf("\n\flow mach no at exit : %f \n\n",Me)
\ No newline at end of file diff --git a/548/CH9/EX9.5/9_05.sce b/548/CH9/EX9.5/9_05.sce new file mode 100755 index 000000000..d067092c3 --- /dev/null +++ b/548/CH9/EX9.5/9_05.sce @@ -0,0 +1,6 @@ +pathname=get_absolute_file_path('9_05.sce')
+filename=pathname+filesep()+'9_05data.sci'
+exec(filename)
+printf("\n\burnout velocity of single stage rocket : %f m/s\n\n",Vb)
+printf("\n\burnout velocity of double stage rocket after second stage: %f m/s\n\n",Vb2)
+disp("As we can see from final burnout velocities that a double-stage rocket can give a greater launching velocity as compared to single stage rocket." )
\ No newline at end of file diff --git a/548/DEPENDENCIES/10_01data.sci b/548/DEPENDENCIES/10_01data.sci new file mode 100755 index 000000000..df480fa91 --- /dev/null +++ b/548/DEPENDENCIES/10_01data.sci @@ -0,0 +1,8 @@ +//consider a rod of stainless steel.
+D=0.01905;//diameter(meter) of the rod
+l=2.54;//length(meter) of the rod
+T=53378.66;//Applied load(N) on the rod
+Y=0.2*10^7;//young's modulous of the rod
+sigma=T/(%pi*D^2*10^5/4) //tensile stress(bar) on the rod
+//as the value of tensile stress is less than tensile yield stress Hook's law can be applied,so :
+strain=sigma/Y //strain on the rod
\ No newline at end of file diff --git a/548/DEPENDENCIES/10_02data.sci b/548/DEPENDENCIES/10_02data.sci new file mode 100755 index 000000000..ca86c3997 --- /dev/null +++ b/548/DEPENDENCIES/10_02data.sci @@ -0,0 +1,6 @@ +//consider an aluminium rod.
+D=6.35*10^-3;//diameter(meter) of the rod
+T=11125;//Applied load(N) on the rod
+Sty=3103;//yield tensile stress(bar)of aluminium rod
+Stu=4206;//ultimate tensile stress(bar)of aluminium rod
+sigma=T/(%pi*D^2*10^5/4) //tensile stress(bar) on the rod
diff --git a/548/DEPENDENCIES/11_01data.sci b/548/DEPENDENCIES/11_01data.sci new file mode 100755 index 000000000..87cd68640 --- /dev/null +++ b/548/DEPENDENCIES/11_01data.sci @@ -0,0 +1,10 @@ +//Refer to figure 11.1.
+M=25;//mach no. of the flow
+//let s denote distance along the sphere surface and R radius than say s/R=r
+r=0.6;//location of point 1 from stagnation point
+phi=57.3*r //location of point 1 in degrees
+theta=(90-phi)*%pi/180 //angle(in radian) made by the line tangent to the body at point 1 w.r.t free stream
+y=1.4;//specific heat ratio of air
+//let pressure behind the normal shock wave is Po2 and free stream pressure p. Then Po2/P=Rp:
+Rp=[(y+1)^2*M^2/(4*y*M^2-2*(y-1))]^(y/(y-1))*[(1-y+2*y*M^2)/(y+1)]
+Cpmax=2*(Rp-1)/(y*M^2) //maximum pressure coefficient
\ No newline at end of file diff --git a/548/DEPENDENCIES/2_1data.sci b/548/DEPENDENCIES/2_1data.sci new file mode 100755 index 000000000..f13cf2da6 --- /dev/null +++ b/548/DEPENDENCIES/2_1data.sci @@ -0,0 +1,5 @@ +//example 2.1: The air pressure and density at a point on the wing of a Boeing 747 are 1.10 * 10^5 N/m^2 and 1.20kg/m^3,respectively.what is temperature at that point?
+p=1.10*10^5;//given
+density=1.20;//given
+R=287;// gas constant.for air(j/kg.k)
+T=p/((density)*(R))
\ No newline at end of file diff --git a/548/DEPENDENCIES/2_2data.sci b/548/DEPENDENCIES/2_2data.sci new file mode 100755 index 000000000..ff3ad485c --- /dev/null +++ b/548/DEPENDENCIES/2_2data.sci @@ -0,0 +1,8 @@ +//example2.2: The high pressure storage tank for a supersonic wind tunnel has a volume of 28.317 m^3.if air is stored at a pressure of 30 atm and a temperature of 299.44K,what is the mass of gas stored in the tank in Kg,and pound mass.
+P=30*1.013*10^5;//1 atm=1.013*10^5 Pascal
+R=287;//gas constant for air(J/Kg-K)
+T=294.44 ;//temperature
+density=P/(R*T);
+V=28.317 ;//volume
+M=density*V;//in kg
+M1=2.20*M;//in pound
\ No newline at end of file diff --git a/548/DEPENDENCIES/2_3data.sci b/548/DEPENDENCIES/2_3data.sci new file mode 100755 index 000000000..66e4c6941 --- /dev/null +++ b/548/DEPENDENCIES/2_3data.sci @@ -0,0 +1,8 @@ +//Air flowing at high speed in a wind tunnel has a pressure and temperature equal to 0.3 atm and -100 degree celcius,respectively.what is specific volme?
+//1 atm=1.01*10^5 Pa or N/m^2
+P=.3*1.01*10^5;//in N/m^2
+//0 degree=273 Kelvin
+T=-100+273;//in Kelvin
+R=287;//gas constant for air.(j/kg.k)
+density=P/(R*T)
+v=1/density
\ No newline at end of file diff --git a/548/DEPENDENCIES/2_4data.sci b/548/DEPENDENCIES/2_4data.sci new file mode 100755 index 000000000..c0f10d6bc --- /dev/null +++ b/548/DEPENDENCIES/2_4data.sci @@ -0,0 +1,5 @@ +//Example 2.4
+P=1.04*10^4//unit N/m^2
+R=287;//gas constant.of air(j/kg.k)
+T=362;//unit K
+density=P/(R*T)
diff --git a/548/DEPENDENCIES/2_5data.sci b/548/DEPENDENCIES/2_5data.sci new file mode 100755 index 000000000..120e105e2 --- /dev/null +++ b/548/DEPENDENCIES/2_5data.sci @@ -0,0 +1,3 @@ +//Example 2.4 :deals with the conversion of units from one system to another
+WingLoading=280.8;//unit Kgf/m^2
+//1 ft=0.3048 m ,1lb=4.448N, 1 Kgf=9.8 N
\ No newline at end of file diff --git a/548/DEPENDENCIES/2_6data.sci b/548/DEPENDENCIES/2_6data.sci new file mode 100755 index 000000000..30836b83a --- /dev/null +++ b/548/DEPENDENCIES/2_6data.sci @@ -0,0 +1,5 @@ +//example 2.6:deals with the conversion of units; a piper cub airplane is flying at 60 mile per hour,convert its velocity in terms of ft/s and m/s
+//1 mile=5280 ft,1 hour=3600 second,1 mile=1609.344
+
+//Velocity in mile/hr:
+V=60;
diff --git a/548/DEPENDENCIES/3_01data.sci b/548/DEPENDENCIES/3_01data.sci new file mode 100755 index 000000000..9101055bd --- /dev/null +++ b/548/DEPENDENCIES/3_01data.sci @@ -0,0 +1,14 @@ +//Temperature remains constant from 11 to 14 Km,so we are about to find pressure and density at a height of 11 Km.
+T=216.66;//temp from 11 to 14 Km
+T1=288.16;//sea level temperature
+P1=1.01*10^5;//pressure at sea level in N/m^2
+D1=1.23;//density at sea level in Kg/m^3
+g=9.8;//earth's gravity in m/s^2
+R=287;//gas constant for dry air in J/Kg.K
+a=(216.66-288.16)/(1000*(11-0)) //Lapse rate from 0 to 11 Km
+P=(P1)*(T/T1)^(-g/(a*R))//pressure at 11 Km
+D=(D1)*(T/T1)^(-1*(g/(a*R)+1))//density at 11 Km
+//as T is constant from 11 to 14 km we can use isothermal relation
+h=14000;h1=11000;//height in meter
+P2=P*(%e)^[-g*(h-h1)/(R*T)]//pressure at 14 Km
+D2=D*P2/P //density at 14 Km
\ No newline at end of file diff --git a/548/DEPENDENCIES/3_02data.sci b/548/DEPENDENCIES/3_02data.sci new file mode 100755 index 000000000..de42fdc4d --- /dev/null +++ b/548/DEPENDENCIES/3_02data.sci @@ -0,0 +1,9 @@ +//datas are all taken from standard table of variation of temperature,pressure and density with height.
+//Pressure at the flying altitude:
+P=4.72*10^4;//in N/m^2
+P1=6;//height corresponding to pressure P in Km
+//Temperature at the flying altitude:
+T=255.7;//in Kelvin
+T1=5//height corresponding to temperature T in Km
+D=P/(R*T)//density at that height
+D1=6.24//height corresponding to density D in Km
diff --git a/548/DEPENDENCIES/3_03data.sci b/548/DEPENDENCIES/3_03data.sci new file mode 100755 index 000000000..59bbbdff8 --- /dev/null +++ b/548/DEPENDENCIES/3_03data.sci @@ -0,0 +1,8 @@ +
+P1=9144//Pressure altitude in Km
+P=0.3*10^5//corresponding pressure at pressure altitude in N/m^2
+//density altitude:
+D1=8686.8//density altitude in Km
+D=0.485//corresponding density at sensity altitude in Kg/m^3
+//Temperature at that altitude:
+T=P/(D*R)//from equation of state
\ No newline at end of file diff --git a/548/DEPENDENCIES/3_04data.sci b/548/DEPENDENCIES/3_04data.sci new file mode 100755 index 000000000..0f41523a0 --- /dev/null +++ b/548/DEPENDENCIES/3_04data.sci @@ -0,0 +1,15 @@ +P=5.3*10^4;//ambient pressure in N/m^2
+T=253;//ambient temperature in K
+R=287;// gas constant for dry air in J/Kg.K
+D=P/(R*T)
+//as we do not have this value of pressure and density from standard table we will take two nearest value and interpolate to get the desired result.
+H1=5100;
+P1=5.331*10^4;//pressure corresponding to H1
+H2=5200;
+P2=5.2621*10^4;//pressure corresponding to H2
+Hp=H1+[(H2-H1)*((P1-P)/(P1-P2))]//pressure altitude corresponding to p
+H3=5000;
+D3=0.73643;//density corresponding to H3 in Kg/m^3
+H4=5100;
+D4=0.72851;//density corresponding to H4 in Kg/m^3
+Hd=H3+[(H4-H3)*((D3-D)/(D3-D4))] //density altitude
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_01data.sci b/548/DEPENDENCIES/4_01data.sci new file mode 100755 index 000000000..dd8aefd98 --- /dev/null +++ b/548/DEPENDENCIES/4_01data.sci @@ -0,0 +1,5 @@ +//this example deals with basic of incompressible flow
+A1=5;//convergent duct inlet area in m^2
+V1=10;//inlet velocity in m/s
+V2=30;//outlet velocity in m/s
+A2=A1*V1/V2//area of duct exit
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_02data.sci b/548/DEPENDENCIES/4_02data.sci new file mode 100755 index 000000000..e8b2b18a5 --- /dev/null +++ b/548/DEPENDENCIES/4_02data.sci @@ -0,0 +1,7 @@ +A1=0.08;//convergent duct with inlet area in m^2
+A2=0.771;//exit area
+D1=1.23;//density of air at inlet
+V1=210;//inlet velocity of air
+V2=321;//outlet velocity of air
+//as inlet velocity of 210 m/s is high speed flow density will vary
+D2=(A1*V1*D1)/(A2*V2) //density of air at the exit duct
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_03data.sci b/548/DEPENDENCIES/4_03data.sci new file mode 100755 index 000000000..8da6c5376 --- /dev/null +++ b/548/DEPENDENCIES/4_03data.sci @@ -0,0 +1,8 @@ +//Application of Bernoulli's equation.an airfoil placed in a flow of air
+P1=1.013;//pressure at far upstream of airfoil in bar
+V1=160*5/18 //velocity at far upstream of airfoil in m/s
+D=1.23;//density at far upstream of airfoil in Kg/m^3
+Pa=0.99;//pressure at a point Aon airfoil in bar
+//velocity is low enough so we can assume incompressible flow,so
+disp("P1+(D*V1^2/2)=Pa+(D*V2^2/2)","Bernoulli equation");
+Va=[(2*(P1-Pa)/D)+(V1)^2]^0.5
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_04data.sci b/548/DEPENDENCIES/4_04data.sci new file mode 100755 index 000000000..c736b2a5d --- /dev/null +++ b/548/DEPENDENCIES/4_04data.sci @@ -0,0 +1,8 @@ +A1=5;//convergent duct inlet area in m^2
+V1=10;//inlet velocity in m/s
+P1=1.2*10^5; //inlet pressure in N/m^2
+T1=330;//inlet temperature in Kelvin
+R=287;//gas constant for dry air
+D=P1/(R*T1) //density of air in Kg/m^3
+V2=30;//outlet velocity in m/s
+P2=P1+D*(V1^2-V2^2)/2 //pressure at exit
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_05data.sci b/548/DEPENDENCIES/4_05data.sci new file mode 100755 index 000000000..0a9d4e207 --- /dev/null +++ b/548/DEPENDENCIES/4_05data.sci @@ -0,0 +1,3 @@ +R=0.1524;//radius(m) of semicircular cross section
+V=30.48;//velocity(m/s) of free stream
+D=1.23;//density(Kg/m^3)of free stream
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_06data.sci b/548/DEPENDENCIES/4_06data.sci new file mode 100755 index 000000000..e6b472c6a --- /dev/null +++ b/548/DEPENDENCIES/4_06data.sci @@ -0,0 +1,13 @@ +//Based on elementary Thermodynamics
+//Part 1:SI unit
+Cv=720;//specific heat at constant volume for air in standard condition in J/Kg.K
+Cp=1008;//specific heat at constant pressure for air in standard condition in J/Kg.K
+T=288;//standard temperature
+e=Cv*T//internal energy per unit mass
+h=Cp*T//enthalpy per unit mass
+//Part 2:English Engineering unit
+Cv1=4290;//specific heat at constant volume for air in Ft.Lb/slug*Rankine
+Cp1=6006;///specific heat at constant volume for air in Ft.Lb/slug*Rankine
+T1=519;//standard temperature in degree rankine
+e1=Cv1*T1//internal energy per unit mass
+h1=Cp1*T1//enthalpy per unit mass
diff --git a/548/DEPENDENCIES/4_07data.sci b/548/DEPENDENCIES/4_07data.sci new file mode 100755 index 000000000..7d6069dff --- /dev/null +++ b/548/DEPENDENCIES/4_07data.sci @@ -0,0 +1,8 @@ +//An airplane is flying at standard sea level condition.
+//The flow conditions are assumed to be isentropic in nature.
+T=250;//temperature at a point on wing in Kelvin
+P1=1.01*10^5;//pressure at far upstream of wing
+T1=288.16;//temperature at far upstream of wing
+y=1.4;//ratio of specific heats for air
+
+
diff --git a/548/DEPENDENCIES/4_08data.sci b/548/DEPENDENCIES/4_08data.sci new file mode 100755 index 000000000..4b72a187b --- /dev/null +++ b/548/DEPENDENCIES/4_08data.sci @@ -0,0 +1,7 @@ +//The flow conditions are assumed to be isentropic in nature.
+P1=20; //pressure of burned gas in combustion chamber in atm unit
+T1=3500; //temperature of the burned gas in combustion chamber in degree kelvin
+P2=0.5; //pressure of the gas at exit in atm
+y=1.15; //specific heat ratio for the gas
+
+
diff --git a/548/DEPENDENCIES/4_09data.sci b/548/DEPENDENCIES/4_09data.sci new file mode 100755 index 000000000..e4c7ccbf8 --- /dev/null +++ b/548/DEPENDENCIES/4_09data.sci @@ -0,0 +1,13 @@ +//deals with properties of air flow through supersonic wind tunnel
+To=1000; //air temperature at the reservior of wind tunnel in degree Kelvin
+Po=10*1.01*10^5; // air pressure at the reservior of wind tunnel in N/m^2
+R=287; //gas constant for air
+Do=Po/(R*To) //density at the reservior
+Te=300; //static temperature at the exit in degree Kelvin
+y=1.4;// specific heat ratio for air
+T1=833; //temperature at the throat in degree Kelvin
+Te=300; //temperature at the exit in degree Kelvin
+D1=Do*(T1/To)^(1/(y-1)) //density at the throat
+Mt=0.5; //mass flow rate through nozzle,Kg/s
+Cp=1008; //specific heat at constant pressure for air,J/Kg.K
+De=Do*(Te/To)^(1/(y-1))
diff --git a/548/DEPENDENCIES/4_10data.sci b/548/DEPENDENCIES/4_10data.sci new file mode 100755 index 000000000..f7368c609 --- /dev/null +++ b/548/DEPENDENCIES/4_10data.sci @@ -0,0 +1,13 @@ +//Consider an airfoil in a flow of air,where far ahead of airfoil conditions are given.
+//the condition for pressure and velocity are not in SI unit so we need to convert it to SI unit.
+P=1.013*1.01*10^5 //pressure far ahead of airfoil in N/m^2
+V=804.7*5/18 //velocity far ahead of airfoil in m/s
+D=1.23; //density in kg/m^3
+R=287;//gas constant for air,J/Kg.K
+T=P/(D*R) //Temperature far ahead of airfoil in degree Kelvin
+Pa=0.716*1.01*10^5 //pressure at a given point A on airfoil
+Cp=1008; //for air specific heat at constant pressure,J/Kg.K
+y=1.4;// specific heat ratio for air
+//Assuming isentropic flow:
+Ta=T*(Pa/P)^((y-1)/y) //temperature at the given point A on airfoil
+
diff --git a/548/DEPENDENCIES/4_11data.sci b/548/DEPENDENCIES/4_11data.sci new file mode 100755 index 000000000..f78af2616 --- /dev/null +++ b/548/DEPENDENCIES/4_11data.sci @@ -0,0 +1,7 @@ +H=9144;//standard altitude of flying in metre
+//from relation of altitude and Temperature:
+T=228.81;//Temperature at Standard altitude of 9144 m
+V=885.14*5/18; //velocity of jet transport
+R=287;//gas constant for air,J/Kg.K
+y=1.4;// specific heat ratio for air
+a=(y*R*T)^0.5 //velocity of sound at that altitude
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_12data.sci b/548/DEPENDENCIES/4_12data.sci new file mode 100755 index 000000000..49ec49944 --- /dev/null +++ b/548/DEPENDENCIES/4_12data.sci @@ -0,0 +1,9 @@ +//Nozzle flow was described in example 4.9,so we can take data from eg 4.9
+V1=580 //velocity at throat,m/s
+Ve=1188 //velocity at exit,m/s
+T1=833 //Temperature at throat,in Kelvin
+Te=300 //Temperature at exit,in kelvin
+R=287;//gas constant for air,J/Kg.K
+y=1.4;// specific heat ratio for air
+a=(y*R*T1)^0.5 //speed of sound at throat
+Ae=(y*R*Te)^0.5 //speed of sound at exit
diff --git a/548/DEPENDENCIES/4_13data.sci b/548/DEPENDENCIES/4_13data.sci new file mode 100755 index 000000000..1472782ca --- /dev/null +++ b/548/DEPENDENCIES/4_13data.sci @@ -0,0 +1,10 @@ +//In A low Speed subsonic wind tunnel,one side of a Mercury manometer is connected byto the reservior and the other side is connected to the test section.
+r=1/15; //contraction ratio of nozzle A2/A1
+P1=1.1*1.01*10^5 //reservior pressure,N/m^2
+T1=300 //reseroir temperature,k
+Dh=0.1 //height difference between the two coloumns of mercury in meter
+D=1.36*10^4; //density of mercury,Kg/m^3
+g=9.8;
+Dp=D*g*Dh //pressure difference between two coloums P2-P1
+R=287; //gas constant for air,J/Kg.k
+D1=P1/(R*T1) //density of flowing material
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_14data.sci b/548/DEPENDENCIES/4_14data.sci new file mode 100755 index 000000000..9beb41a96 --- /dev/null +++ b/548/DEPENDENCIES/4_14data.sci @@ -0,0 +1,8 @@ +//Consider a low subsonic wind tunnel.
+A1=2; //reservoir area,m^2
+A2=0.5; //test section area,m^2
+P2=1.01*10^5;//test section pressure,N/m^2
+V2=40;//flow velocity in test section
+//from continuity equation
+V1=V2*(A2/A1)//velocity before test section
+D=1.23; //density of flow equals standard sea level,Kg/m^3
diff --git a/548/DEPENDENCIES/4_15data.sci b/548/DEPENDENCIES/4_15data.sci new file mode 100755 index 000000000..87422fd2d --- /dev/null +++ b/548/DEPENDENCIES/4_15data.sci @@ -0,0 +1,6 @@ +//example 4.15 a/if P1-P2 ((1.019-1.01)*10^5) in example 4.14 is doubled what is the flow velocity in test section?b/if contraction ratio A1/A2 (2/.5) is doubled then what is the flow velocity in test section?
+V=40; //initial velocity in test section,m/s
+r=4; // A1/A2=2/0.5=4
+R=8 ;//doubled value of A1/A2
+Dp=(1.019-1.01)*10^5; //intial value of pressure difference
+D=1.23; //density,Kg/m^3
diff --git a/548/DEPENDENCIES/4_16data.sci b/548/DEPENDENCIES/4_16data.sci new file mode 100755 index 000000000..225ffb3c0 --- /dev/null +++ b/548/DEPENDENCIES/4_16data.sci @@ -0,0 +1,8 @@ +//pressure units are converted from bar to N/m^2
+Hp=1524 ;//pressure altitude
+P=0.8432*10^5 //From the standard atmosphere Table at 1524 meter,N/m^2
+Po=0.87*10^5 ;//total pressure in N/m^2
+R=287 ;//gas constant for air,J/Kg.K
+T=280.56 ;//outside temperature,Kelvin
+D=P/(R*T) //density,Kg/m^3
+Ds=1.226 ;//standard sea level density,Kg/m^3
diff --git a/548/DEPENDENCIES/4_17data.sci b/548/DEPENDENCIES/4_17data.sci new file mode 100755 index 000000000..862da2394 --- /dev/null +++ b/548/DEPENDENCIES/4_17data.sci @@ -0,0 +1,10 @@ +Hp=10000; //pressure altitude in m
+Po=4.24*10^4; //Total pressure measured by pitot tube,N/m^2
+P1=2.65*10^4; //pressure at pressure altitude 10000m from standard atmospheric table,N/m^2
+T=230; //ambient temperature in Kelvin
+R=287 ;//gas constant for air,J/Kg.K
+y=1.4; //specific heat ratio for air
+a=340.3; //speed of sound at sea level,m/s
+P=1.01*10^5 ;//stmospheric pressure at sea level
+
+
diff --git a/548/DEPENDENCIES/4_18data.sci b/548/DEPENDENCIES/4_18data.sci new file mode 100755 index 000000000..d01575a53 --- /dev/null +++ b/548/DEPENDENCIES/4_18data.sci @@ -0,0 +1,7 @@ +V=4828.03*5/18//data for velocity is given in Kmph,to convert it to m/s multiply it by 5/18
+P=0.0723*10^5;// ambient pressure,N/m^2
+T=216.66;//ambient temperature in Kelvin
+R=287 ;//gas constant,J/Kg.K
+y=1.4; //specific heat ratio for air
+M=V/(y*R*T)^0.5 //Mach number
+//as M>1 so the flow is supersonic
diff --git a/548/DEPENDENCIES/4_19data.sci b/548/DEPENDENCIES/4_19data.sci new file mode 100755 index 000000000..cadbd2a4f --- /dev/null +++ b/548/DEPENDENCIES/4_19data.sci @@ -0,0 +1,15 @@ +//Assume the flow to be isentropic
+P=1.013*10^5; //free-stream pressure,N/m^2
+V=804.7*5/18; //free-stream velocity,m/s
+D=1.23; //density,Kg/m^3
+Pa=0.7167*10^5; //pressure at a point on airfoil
+R=287 ;//gas constant,J/Kg.K
+y=1.4; //specific heat ratio for air
+T=P/(D*R) //free stream temperature
+a=sqrt(y*R*T)//speed of sound at free stream temperature
+M=V/a //free stream mach no.
+To=T*(1+(y-1)*M^2/2) //free stream total temperature
+Po=P*(1+(y-1)*M^2/2)^(y/(y-1)) //free stream total pressure
+Poa=Po;//since the total presssure remains same inisentropic flow
+Toa=To;//since the total temperature remains same inisentropic flow
+
diff --git a/548/DEPENDENCIES/4_20data.sci b/548/DEPENDENCIES/4_20data.sci new file mode 100755 index 000000000..c0667382f --- /dev/null +++ b/548/DEPENDENCIES/4_20data.sci @@ -0,0 +1,6 @@ +Me=2; //mach no in test section at standard sea level condition
+//following are the standard sea level conditions desired at the exit of nozzle:
+Pe=1.01*10^5;//static pressure,N/m^2
+Te=288.16; //static temperature in Kelvin
+y=1.4; //specific heat ratio for air
+A=1+(y-1)*Me^2/2
diff --git a/548/DEPENDENCIES/4_21data.sci b/548/DEPENDENCIES/4_21data.sci new file mode 100755 index 000000000..8f3d85ca8 --- /dev/null +++ b/548/DEPENDENCIES/4_21data.sci @@ -0,0 +1,9 @@ +//in question pressure given is 1.013*10^5 but while solving it uses
+//10*1.013*10^5,so we use the later.
+Po=10*1.013*10^5 ;//reservoir pressure in Pascal
+To=333.33; //reservoir temperature in Kelvin
+Me=3;//mach no. at test section
+y=1.4; //specific heat ratio for air
+R=287 ;//gas constant,J/Kg.K
+Pe=Po*[1+(y-1)*Me^2/2]^((-y)/(y-1)) //exit pressure
+Tstag=To //the stagnation point temperature remains same as that of total temperature(reservoir temperature) througout the compression
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_22data.sci b/548/DEPENDENCIES/4_22data.sci new file mode 100755 index 000000000..6d8ddb5fa --- /dev/null +++ b/548/DEPENDENCIES/4_22data.sci @@ -0,0 +1,16 @@ +//consider the combustion chamber condition as reservoir
+Po=20*1.01*10^5;//combustion chamber pressure in N/m^2
+To=3144;//combustion chamber temperature in Kelvin
+R=378;//gas constant for mixture of kerosene and oxygen
+y=1.26;//specific heat ratio
+Pe=1*1.01*10^5//pressure at exit of rocket Nozzle in N/m^2
+At=0.1;//throat area in m^2
+Te=To*(Pe/Po)^((y-1)/y) //temperature at exit in degree kelvin
+Me=sqrt(2*((To/Te)-1)/(y-1)) //mach no. at the exit
+Ae=sqrt(y*R*Te) //speed of sound at exit,m/s
+Mt=1;//Mach no. at throat
+Pt=Po/(1+(y-1)*Mt^2/2)^(y/(y-1)) //pressure at throatin N/m^2
+Tt=To/(1+(y-1)*Mt^2/2) //temperature at throat in Kelvin
+Dt=Pt/(R*Tt) //density of gas in throat,Kg/m^3
+Vt=sqrt(y*R*Tt) //speed of sount in throat which is equivalent to gas speed as mach no. at throat is 1.
+
diff --git a/548/DEPENDENCIES/4_23data.sci b/548/DEPENDENCIES/4_23data.sci new file mode 100755 index 000000000..cc5ed25ff --- /dev/null +++ b/548/DEPENDENCIES/4_23data.sci @@ -0,0 +1,10 @@ +//consider the flow of air over a small flat plate that is 5 cm long in flow direction and 1m wide.free stream conditions corresponds to standard sea level condition
+V=120; //flow velocity,m/s
+D=1.225;//free stream density,Kg/m^3
+x=0.05 ;//length of plate in meter
+w=1;//width of plate in meter
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+Re=D*V*x/u //Reynolds Number at trailing edge
+Cf=1.328/Re^0.5 //Skin friction drag coefficient
+q=D*V^2/2 //dynamic pressure at outer edge of boundary,N/m^2
+S=x*w;//area of plate,m^2
diff --git a/548/DEPENDENCIES/4_24data.sci b/548/DEPENDENCIES/4_24data.sci new file mode 100755 index 000000000..24e617301 --- /dev/null +++ b/548/DEPENDENCIES/4_24data.sci @@ -0,0 +1,14 @@ +//consider the flow of air over a small flat plate that is 5 cm long in flow direction and 1m wide.free stream conditions corresponds to standard sea level condition
+V=120; //flow velocity,m/s
+D=1.225;//free stream density,Kg/m^3
+x=0.05 ;//length of plate in meter
+w=1;//width of plate in meter
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+//reynolds no at 1 cm:
+Re1=D*V*.01/u
+//reynolds no at 5 cm:
+Re2=D*V*.05/u
+Cf1=0.664/Re1^0.5 //Skin friction drag coefficient at 1 cm
+Cf2=0.664/Re2^0.5 //Skin friction drag coefficient at 5 cm
+q=D*V^2/2 //dynamic pressure at outer edge of boundary,N/m^2
+
diff --git a/548/DEPENDENCIES/4_25data.sci b/548/DEPENDENCIES/4_25data.sci new file mode 100755 index 000000000..b6cbda362 --- /dev/null +++ b/548/DEPENDENCIES/4_25data.sci @@ -0,0 +1,12 @@ +//consider the flow same as in example 4.23,but assume boundaary layer is noe completely turbulent.
+//datas are taken from example 4.23:
+V=120; //flow velocity,m/s
+D=1.225;//free stream density,Kg/m^3
+x=0.05 ;//length of plate in meter
+w=1;//width of plate in meter
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+Re=D*V*x/u //Reynolds Number at trailing edge
+Cf=0.074/Re^0.2 //Skin friction drag
+q=D*V^2/2 //dynamic pressure at outer edge of boundary,N/m^2
+S=x*w;//area of plate,m^2
+
diff --git a/548/DEPENDENCIES/4_26data.sci b/548/DEPENDENCIES/4_26data.sci new file mode 100755 index 000000000..c47659d40 --- /dev/null +++ b/548/DEPENDENCIES/4_26data.sci @@ -0,0 +1,15 @@ +//repeatation of example 4.24,expect boundary layer is completely turbulent.
+//datas taken from example 4.24:
+V=120; //flow velocity,m/s
+D=1.225;//free stream density,Kg/m^3
+x=0.05 ;//length of plate in meter
+w=1;//width of plate in meter
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+//reynolds no at 1 cm:
+Re1=D*V*.01/u
+//reynolds no at 5 cm:
+Re2=D*V*.05/u
+Cf1=0.0592/Re1^0.2 //Skin friction drag coefficient at 1 cm
+Cf2=0.0592/Re2^0.2 //Skin friction drag coefficient at 5 cm
+q=D*V^2/2 //dynamic pressure at outer edge of boundary,N/m^2
+
diff --git a/548/DEPENDENCIES/4_27data.sci b/548/DEPENDENCIES/4_27data.sci new file mode 100755 index 000000000..e44b459f2 --- /dev/null +++ b/548/DEPENDENCIES/4_27data.sci @@ -0,0 +1,16 @@ +//assume the boundary layer over the wing is turbulent
+H=10668 ;//standard altitude at which F-104 is flying in meter
+M=2;//Mach No.at which plane is flying
+x=0.6096;//shear stress to be calculated at this distance downstream of leading edge
+y=1.4; //specific heat ratio for air
+R=287 ;//gas constant,J/Kg.K
+//following are the datas at standard altitude of 10668 meter from standard tables
+D=0.3807;//density,Kg/m^3
+T=218.93;//temperature,Kelvin
+V=(y*R*T)^0.5*M //velocity of the plane
+u=1.35*10^-5;//viscosity from standard table of variation of u versus T in kg/(m)(s)
+Re=D*V*0.6096/u //reynolds no at 0.6096 meter:
+Cfx=0.0592/Re^0.2 //incompressible skin fraction coefficient
+//for mach 2 ratio of Cf/Cfx=0.2,so
+Cf=0.74*Cfx //skin friction coefficient
+q=D*V^2/2 //dynamic pressure
\ No newline at end of file diff --git a/548/DEPENDENCIES/4_28data.sci b/548/DEPENDENCIES/4_28data.sci new file mode 100755 index 000000000..96baa8567 --- /dev/null +++ b/548/DEPENDENCIES/4_28data.sci @@ -0,0 +1,15 @@ +//In this example flow over the wing is both turbulent and laminar.so to find drag we need to find drag on both laminar and turbulent layer and add them.
+b=12.202;//wing span in meter
+S=23.69;//wing area in m^2
+c=S/b //wing width
+Ret=6.5*10^5;//transition reynolds number or critical reynolds number
+D=1.225;//density at standard sea level,Kg/m^3
+u=1.79*10^-5;//Viscosity in at standard sea level in kg/(m)(s)
+V=48.3*5/18 //velocity of flyer
+q=D*V^2/2 //dynamic pressure
+Re=D*V*c/u //reynolds no. at trailing edge
+Xcr=(Ret*u)/(D*V) //distance from leading edge where transition occur
+A=Xcr*b //area over which laminar flow occur in m^2
+B=(c-Xcr)*b //area over which turbulent flow occur in m^2
+
+
diff --git a/548/DEPENDENCIES/5_01data.sci b/548/DEPENDENCIES/5_01data.sci new file mode 100755 index 000000000..8760cd0b1 --- /dev/null +++ b/548/DEPENDENCIES/5_01data.sci @@ -0,0 +1,13 @@ +//A model wing is placed in a low speed subsonic wind tunnel.the wing has a NACA-2412 airfoil.
+c=1.3;//chord length in meter
+V=50; // velocity of flow in test section(m/s)
+a=4;//angle of attack in degree
+D=1.225;//standard sea level density,Kg/m^3
+u=1.789*10^-5;//Viscosity in kg/(m)(s)
+//from standard table for NACA-2412 airfoil with angle of attack 4 degree:
+Cl=0.63;//Lift coefficient
+Cm=-0.035;//moment coefficient about quarter chord
+Re=D*V*c/u //reynold's no.
+//from the value of Re and angle of attack and by using standard table we can get Cd:
+Cd=0.007;//coefficient of drag
+q=D*V^2/2 //dynamic pressure,N/m^2
diff --git a/548/DEPENDENCIES/5_02data.sci b/548/DEPENDENCIES/5_02data.sci new file mode 100755 index 000000000..eaa7c07a3 --- /dev/null +++ b/548/DEPENDENCIES/5_02data.sci @@ -0,0 +1,11 @@ +//consider the same wing configuration as that of example 5.1.
+L=700; //Lift per unit span
+V=50; // velocity of flow in test section(m/s)
+D=1.225;//standard sea level density,Kg/m^3
+q=D*V^2/2 //dynamic pressure,N/m^2
+S=1.3;//wing area,m^2
+Cl=L/(q*S) //coefficient of lift
+//from the value of Cl and wing configuration we can get angle of attack by using standard table:
+a=1 //angle of attack in degree
+//To cause zero lift Cl=0,so from standard table of Cl and Lift:
+a1=-2.2 //angle of attack in degree
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_03data.sci b/548/DEPENDENCIES/5_03data.sci new file mode 100755 index 000000000..34857be9d --- /dev/null +++ b/548/DEPENDENCIES/5_03data.sci @@ -0,0 +1,6 @@ +H=2000;//standard altitude at which airplane is flying(meter)
+P=7.95*10^4;//pressure corresponding to standard altitude,N/m^2
+D=1.0066;//density corresponding to standard altitude,Kg/m^3
+P1=7.58*10^4;//pressure at a point on wing,N/m^2
+V=70;//airplane velocity in m/s
+q=D*V^2/2 //dynamic pressure,N/m^2
diff --git a/548/DEPENDENCIES/5_04data.sci b/548/DEPENDENCIES/5_04data.sci new file mode 100755 index 000000000..82f6c9873 --- /dev/null +++ b/548/DEPENDENCIES/5_04data.sci @@ -0,0 +1,6 @@ +//consider an airfoil mounted in a low speed subsonic wind tunnel.
+V=30.5;//flow velocity in test section(m/s)
+D=1.225;//standard sea level density,Kg/m^3
+P=1.014*10^5;//standard sea level pressure,N/m^2
+P1=1.01*10^5;//pressure at a point on airfoil,N/m^2
+q=D*V^2/2 //dynamic pressure,N/m^2
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_05data.sci b/548/DEPENDENCIES/5_05data.sci new file mode 100755 index 000000000..2145620d1 --- /dev/null +++ b/548/DEPENDENCIES/5_05data.sci @@ -0,0 +1,2 @@ +Cpo=-1.18;//low speed value of pressure coefficient
+M=0.6;//free stream mach number
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_06data.sci b/548/DEPENDENCIES/5_06data.sci new file mode 100755 index 000000000..3745edebf --- /dev/null +++ b/548/DEPENDENCIES/5_06data.sci @@ -0,0 +1,6 @@ +V=100;//velocity of airplane(m/s)
+H=3000;//standard altitude at which airplane is flying(meter)
+Cp=-2.2;//pressure coefficient at a point on fuselage
+P=7.0121*10^4;//pressure at 3000 m,N/m^2
+D=0.90926;//density at 3000 m,Kg/m^3
+q=D*V^2/2 //dynamic pressure,N/m^2
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_07data.sci b/548/DEPENDENCIES/5_07data.sci new file mode 100755 index 000000000..8e2359355 --- /dev/null +++ b/548/DEPENDENCIES/5_07data.sci @@ -0,0 +1,6 @@ +V=80;//velocity of airplane(m/s)
+//propertiess at point 1:
+V1=110;//velocity(m/s)
+Cp1=-1.5;//pressure coefficient
+//propertiess at point 2:
+Cp2=-0.8;//pressure coefficient
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_08data.sci b/548/DEPENDENCIES/5_08data.sci new file mode 100755 index 000000000..27e00ade3 --- /dev/null +++ b/548/DEPENDENCIES/5_08data.sci @@ -0,0 +1,8 @@ +//consider an airfoil with chord length c and the running distance x measured along the chord.The leading edge is located at x/c=0 and the trailing edge x/c=1.
+//pressure coefficient variation(Cpu for upper and Cpl for lower):
+disp("Cpu=1-300*(x/c)^2 for 0<x/c<0.1");
+disp("Cpu=-2.2277+2.2277*(x/c) for 0.1<x/c<1.0");
+disp("Cpl=1-0.95*(x/c) for 0<x/c<1.0");
+//putting the value of x/c as and integrating (Cpl-Cpu)dy from 0 to 1 we will get normal force coefficient Cn
+Cn=integrate('1-0.95*y','y',0,1.0)-integrate('1-300*y^2 ','y',0,0.1)-integrate('-2.2277+2.2277*y','y',0.1,1.0)
+
diff --git a/548/DEPENDENCIES/5_09data.sci b/548/DEPENDENCIES/5_09data.sci new file mode 100755 index 000000000..4fda15fd3 --- /dev/null +++ b/548/DEPENDENCIES/5_09data.sci @@ -0,0 +1,5 @@ +//consider a NACA-4412 airfoil at an angle of attack of 4 degree.
+a=4;//angle of attack in degree
+//from standard table for NACA-4412 airfoil at 4 degree angle of attack we can get lift coefficient(at low speed):
+Co=0.83;//lift coefficient(at low speed)
+M=0.7;//Mach number
diff --git a/548/DEPENDENCIES/5_10_data.sci b/548/DEPENDENCIES/5_10_data.sci new file mode 100755 index 000000000..db2cfaa26 --- /dev/null +++ b/548/DEPENDENCIES/5_10_data.sci @@ -0,0 +1,4 @@ +//consider a NACA-0012 airfoil
+Cpomin=-0.43;//minimum pressure coefficient on the surface of airfoil at low speed from figure of Cp vs x/c given in question.
+M=linspace(0.4,0.9,6);//Mach number over which we have to calculate Cp critical.
+y=1.4;//specific heat ratio for air.
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_11_data.sci b/548/DEPENDENCIES/5_11_data.sci new file mode 100755 index 000000000..e9acdeecb --- /dev/null +++ b/548/DEPENDENCIES/5_11_data.sci @@ -0,0 +1,17 @@ +c=1.524;//chord length of airfoil(meter)
+h=6096;//standard altitude(meter)
+a=5*%pi/180;//angle of attack in radian
+D=0.654;//density at standard altitude of 6096 meter,Kg/m^3
+T=248.6;//temperature at standard altitude of 6096 meter in kelvin
+R=287 ;//gas constant,J/Kg.K
+y=1.4; //specific heat ratio for air
+//for part a (mach no 3):
+M=3;//Mach no.
+q=D*((y*R*T)^0.5*M)^2/2 //dynamic pressure
+Cl=4*a/(M^2-1)^0.5//lift coefficient
+Cd=4*a^2/(M^2-1)^0.5//wave drag coefficient
+//for part b(mach no 2):
+M1=2;//Mach no.
+q1=D*((y*R*T)^0.5*M1)^2/2 //dynamic pressure
+Cl1=4*a/(M1^2-1)^0.5//lift coefficient
+Cd1=4*a^2/(M1^2-1)^0.5//wave drag coefficient
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_12_data.sci b/548/DEPENDENCIES/5_12_data.sci new file mode 100755 index 000000000..083b4f004 --- /dev/null +++ b/548/DEPENDENCIES/5_12_data.sci @@ -0,0 +1,16 @@ +M=2;//mach no at which F-104 is flying
+S=19.5;//wing planform area in m^2
+//in steady flight lift equals to weight so:
+L=7262*9.8 //lift (N)
+R=287 ;//gas constant,J/Kg.K
+y=1.4; //specific heat ratio for air
+//part a(at sea level)
+D=1.23;//density at sea level(Kg/m^3)
+T=288;//sea level temperature(K)
+V=(y*R*T)^0.5*M //velocity at sea level(m/s)
+q=D*V^2/2 //dynamic pressure at sea level
+//part b(at 10 Km)
+D1=0.41351;//density at 10 Km(Kg/m^3)
+T1=223.26;//temperature(K) at 10 Km
+V1=(y*R*T1)^0.5*M //velocity at 10 Km(m/s)
+q1=D1*V1^2/2 //dynamic pressure at 10 Km(N/m^2)
diff --git a/548/DEPENDENCIES/5_13data.sci b/548/DEPENDENCIES/5_13data.sci new file mode 100755 index 000000000..d64699c21 --- /dev/null +++ b/548/DEPENDENCIES/5_13data.sci @@ -0,0 +1,8 @@ +h=10;//flying altitude in Km
+a=10*%pi/180;//angle of attack in radian
+S=19.5;//wing planform area in m^2
+M=2;//mach no
+D=0.41351;//density at 10 Km(Kg/m^3)
+T=223.26;//temperature(K) at 10 Km
+V=(y*R*T1)^0.5*M //velocity at 10 Km(m/s)
+q=D*V^2/2 //dynamic pressure at 10 Km
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_14data.sci b/548/DEPENDENCIES/5_14data.sci new file mode 100755 index 000000000..d5e1a13f5 --- /dev/null +++ b/548/DEPENDENCIES/5_14data.sci @@ -0,0 +1,5 @@ +S=15.79;//wing area in m^2
+L=80000;//lift produced by wing
+V=402.34*5/18;//velocity of airplane(m/s)
+D=1.225;//density at sea level(Kg/m^3)
+q=D*V^2/2 //dynamic pressure at sea level(N/m^2)
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_15data.sci b/548/DEPENDENCIES/5_15data.sci new file mode 100755 index 000000000..87dff71cd --- /dev/null +++ b/548/DEPENDENCIES/5_15data.sci @@ -0,0 +1,6 @@ +b=7.7;//wingspan of the Northrop F-5(m)
+e=0.8;//span efficiency factor
+S=15.79;//wing area in m^2
+AR=b^2/S//aspect ratio
+Cl=0.6622;//lift coefficient(data taken from example 5.14)
+q=7651.224;//dynamic pressure in N/m^2(data taken from example 5.14)
diff --git a/548/DEPENDENCIES/5_16data.sci b/548/DEPENDENCIES/5_16data.sci new file mode 100755 index 000000000..10100b565 --- /dev/null +++ b/548/DEPENDENCIES/5_16data.sci @@ -0,0 +1,12 @@ +S=206;//wing area in m^2
+AR=10;//aspect ratio
+e=0.95;//span efficiency factor
+W=7.5*10^5;//weight of the airplane in newton
+Hd=3;//density altitude in Km
+D=0.909;//density at density altitude of 3 Km(Kg/m^3)
+V=100;//flight velocity(m/s)
+//lift is equivalent to weight,so
+Cl=W/((D*V^2/2)*S)//lift coefficient
+Cdi=Cl^2/(%pi*e*AR) //induced drag coefficient
+Cd=0.006;//profile drag coefficient from estimated from aerodynamic data
+q=(D*V^2/2)
diff --git a/548/DEPENDENCIES/5_17data.sci b/548/DEPENDENCIES/5_17data.sci new file mode 100755 index 000000000..431d4255a --- /dev/null +++ b/548/DEPENDENCIES/5_17data.sci @@ -0,0 +1,13 @@ +//consider a NACA-23012(finite wing)
+Re=5*10^6;//reynold's number
+e=0.95;//span efficiency factor
+AR=10;//aspect ratio
+a=4;//angle of attack in degree
+//for a infinite wing of NACA-23012 airfoil:
+Clo=1.2;//lift coefficient at 10 degree angle of attack
+Cl1=0.14;//lift coefficient at 0 degree angle of attack
+ao=(Clo-Cl1)/10 //infinite wing slope per degree
+a1=ao/(1+57.3*ao/(3.14*e*AR)) //lift slope for finite wing
+a2=-1.5;//angle of attack at zero lift from standard data
+cd=0.006;//profile drag coefficient estimated from aerodynamic data
+
diff --git a/548/DEPENDENCIES/5_18data.sci b/548/DEPENDENCIES/5_18data.sci new file mode 100755 index 000000000..c606985a7 --- /dev/null +++ b/548/DEPENDENCIES/5_18data.sci @@ -0,0 +1,11 @@ +b=12.29;//wing span in meter
+S=23.69;//wing area in m^2
+AR=b^2/S //aspect ratio
+D=1.225;//density at standard sea level,Kg/m^3
+V=48.3*5/18 //velocity of flyer(m/s)
+e=0.93;//span efficiency factor
+W=3337.5;//total weight of the flyer in newton
+L=W/2;//lift on one wing(out of two)in newton
+q=(D*V^2/2) //dynamic pressure(N/m^2)
+Cl=L/(q*S)//lift coefficient
+Cdi=Cl^2/(%pi*e*AR) //induced drag coefficient
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_19data.sci b/548/DEPENDENCIES/5_19data.sci new file mode 100755 index 000000000..492db037c --- /dev/null +++ b/548/DEPENDENCIES/5_19data.sci @@ -0,0 +1,16 @@ +a=2;//angle of attack for both wings
+e=0.95;//span efficiency factor for both wings
+a2=-1.5;//angle of attack at zero lift from standard data(also used in example 5.17)
+//part a. for the airfoil of aspect ratio 4:
+AR1=4;//aspect ratio.
+ao=0.106;//infinite wing slope per degree (from example 5.17)
+a1=ao/(1+57.3*ao/(%pi*e*AR1)) //lift slope for finite wing
+Cl=a1*(a-a2) //lift coefficient at 2 degree
+Cl1=a1*(a+0.5-a2) //lift coefficient at 2.5 degree
+Dcl=Cl1-Cl //change in lift coefficient for wing 1(aspect ratio 4)
+
+//part b. for airfoil of aspect ratio 10:
+a11=0.088;//lift slope for finite wing per degree for aspect ratio 10(from example 5.17)
+Cl2=a11*(a-a2)//lift coefficient at 2 degree
+Cl22=a11*(a+0.5-a2) //lift coefficient at 2.5 degree
+Dcl2=Cl22-Cl2 //change in lift coefficient for wing 2(aspect ratio 10)
\ No newline at end of file diff --git a/548/DEPENDENCIES/5_20data.sci b/548/DEPENDENCIES/5_20data.sci new file mode 100755 index 000000000..89c733652 --- /dev/null +++ b/548/DEPENDENCIES/5_20data.sci @@ -0,0 +1,5 @@ +Wt=10258*9.8;//total weight of plane including fuel (unit N)
+Wf=6071*9.8;//weight without fuel (unit N)
+D=1.23;//density at sea level(Kg/m^3)
+S=18.21;//wing area in m^2
+Clm=1.15;//maximum lift coefficient at subsonic speed
diff --git a/548/DEPENDENCIES/5_21data.sci b/548/DEPENDENCIES/5_21data.sci new file mode 100755 index 000000000..f21fcfd66 --- /dev/null +++ b/548/DEPENDENCIES/5_21data.sci @@ -0,0 +1,4 @@ +Wt=712000;//total weight of plane including fuel (unit N)
+D=1.225;//density at sea level(Kg/m^3)
+S=153.29;//wing area in m^2
+Clm=3;//maximum lift coefficient at subsonic speed
diff --git a/548/DEPENDENCIES/602data.sci b/548/DEPENDENCIES/602data.sci new file mode 100755 index 000000000..9546dfb23 --- /dev/null +++ b/548/DEPENDENCIES/602data.sci @@ -0,0 +1,10 @@ +//consider the CJ-1 at sea level.
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=88176.75;//normal gross weight(N)
+Tf=2*16245//thrust (N) provided by two turbofan engine
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+V=linspace(40,300,500);//velocity over which we have to find thrust(40 to 300 m/s and over 500 points)
diff --git a/548/DEPENDENCIES/6_02data.sci b/548/DEPENDENCIES/6_02data.sci new file mode 100755 index 000000000..9546dfb23 --- /dev/null +++ b/548/DEPENDENCIES/6_02data.sci @@ -0,0 +1,10 @@ +//consider the CJ-1 at sea level.
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=88176.75;//normal gross weight(N)
+Tf=2*16245//thrust (N) provided by two turbofan engine
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+V=linspace(40,300,500);//velocity over which we have to find thrust(40 to 300 m/s and over 500 points)
diff --git a/548/DEPENDENCIES/6_05data.sci b/548/DEPENDENCIES/6_05data.sci new file mode 100755 index 000000000..0f9234cfc --- /dev/null +++ b/548/DEPENDENCIES/6_05data.sci @@ -0,0 +1,12 @@ +//for the jet power executive aircraft(CJ-1):
+Tf=2*16245;//thrust (N) provided by both turbofan engine
+Do=1.225;//density(Kg/m^3) at sea level
+D=0.6107;//density(Kg/m^3) at height 6705.6 m
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+W=88176.75;//normal gross weight(N)
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+//in order to find max. velocity we need to find out the intersection of power required curve for example 6.3b and power available curve at height of 6705m:
+
diff --git a/548/DEPENDENCIES/6_06data.sci b/548/DEPENDENCIES/6_06data.sci new file mode 100755 index 000000000..c19862f6b --- /dev/null +++ b/548/DEPENDENCIES/6_06data.sci @@ -0,0 +1,14 @@ +//for the CP-1(datas from example 6.1a):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=13127.5;//normal gross weight(N)
+f=65;//fuel capacity
+P=230;//power provided by piston engine (unit-horsepower(hp))
+Sf=2.0025;//specific fuel consumption(N/(hp.h))
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+Pf=0.8;//propeller efficiency
+V = linspace(30,80,500);//velocity over which we have to find thrust(30 to 400 m/s and over 500 points)
+Pa=P*Pf*746/1000//power available(KN-m/s)
diff --git a/548/DEPENDENCIES/6_07data.sci b/548/DEPENDENCIES/6_07data.sci new file mode 100755 index 000000000..2d07a2af8 --- /dev/null +++ b/548/DEPENDENCIES/6_07data.sci @@ -0,0 +1,3 @@ +//for the Cp-1:
+L_D=13.6;//maximum lift to drag ratio(L/D)
+H=3048;//altitude(m) at which gliding starts.
diff --git a/548/DEPENDENCIES/6_08data.sci b/548/DEPENDENCIES/6_08data.sci new file mode 100755 index 000000000..3e0c2eb59 --- /dev/null +++ b/548/DEPENDENCIES/6_08data.sci @@ -0,0 +1,3 @@ +//for the CJ-1:
+L_D=16.9;//maximum lift to drag ratio(L/D)
+H=3048;//altitude(m) at which gliding starts.
diff --git a/548/DEPENDENCIES/6_09data.sci b/548/DEPENDENCIES/6_09data.sci new file mode 100755 index 000000000..cbea2aa35 --- /dev/null +++ b/548/DEPENDENCIES/6_09data.sci @@ -0,0 +1,8 @@ +//for the CP-1:
+W=13127.5;//normal gross weight(N)
+S=16.165;//wingarea(m^2)
+a=4.2*%pi/180;//approx minimum glide angle(radian).from example 6.7
+D1=0.905;//density at 3048 m(Kg/m^3)
+D2=1.155;//density at 609.6 m(Kg/m^3)
+Cl=0.634;//lift coefficient corresponding to minimum glide angle i.e maximum L/D(from example 6.1)
+Wl=W/S//wing loading (W/S in N/m^2)
diff --git a/548/DEPENDENCIES/6_12data.sci b/548/DEPENDENCIES/6_12data.sci new file mode 100755 index 000000000..97e611f0e --- /dev/null +++ b/548/DEPENDENCIES/6_12data.sci @@ -0,0 +1,10 @@ +//for the cessna skylane(CP-1):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+Wo=13127.5;//normal gross weight(N)
+Wf=1632.5;//weight(N)of fuel
+W1=Wo-Wf//empty weight(N)
+n=0.8;//efficiency
+c=2.0025/(3600*746)//specific fuel consumption(N/(hp.s))
+D=1.225;//density at sea level(Kg/m^3)
diff --git a/548/DEPENDENCIES/6_13data.sci b/548/DEPENDENCIES/6_13data.sci new file mode 100755 index 000000000..cc436fc17 --- /dev/null +++ b/548/DEPENDENCIES/6_13data.sci @@ -0,0 +1,9 @@ +//for the jet power executive aircraft(CJ-1):
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+Wo=88176.75;//normal gross weight(N)
+Wf=33211.9;//weight(N)of fuel
+W1=Wo-Wf//empty weight(N)
+c=0.6/3600//specific fuel consumption(1/s)
+D=0.6107;//density at altitude 6705.6 m(Kg/m^3)
diff --git a/548/DEPENDENCIES/6_14data.sci b/548/DEPENDENCIES/6_14data.sci new file mode 100755 index 000000000..9608be99a --- /dev/null +++ b/548/DEPENDENCIES/6_14data.sci @@ -0,0 +1,6 @@ +//for the cessna skylane(CP-1):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_15data.sci b/548/DEPENDENCIES/6_15data.sci new file mode 100755 index 000000000..3c9acf3ed --- /dev/null +++ b/548/DEPENDENCIES/6_15data.sci @@ -0,0 +1,6 @@ +//for the jet power executive aircraft(CJ-1):
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_16b_data.sci b/548/DEPENDENCIES/6_16b_data.sci new file mode 100755 index 000000000..a26559146 --- /dev/null +++ b/548/DEPENDENCIES/6_16b_data.sci @@ -0,0 +1,13 @@ +//for the cessna skylane(CP-1):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=13127.5;//normal gross weight(N)
+f=65;//fuel capacity
+P=230;//power provided by piston engine (unit-horsepower(hp))
+Sf=2.0025;//specific fuel consumption(N/(hp.h))
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+Pf=0.8;//propeller efficiency
+L_Dmax=13.6;//maximum L/D from example 6.12
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_16c_data.sci b/548/DEPENDENCIES/6_16c_data.sci new file mode 100755 index 000000000..53529655f --- /dev/null +++ b/548/DEPENDENCIES/6_16c_data.sci @@ -0,0 +1,7 @@ +//for the jet power executive aircraft(CJ-1):
+S=29.54;//wingarea(m^2)
+D=1.225;//density at sea level(Kg/m^3)
+W=88176.75;//normal gross weight(N)
+Tf=16245;//thrust (N) provided by single turbofan engine
+Cdo=0.02;//parasite drag coefficient
+L_Dmax=16.9;//maximum L/D ,from example 6.13
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_16d_data.sci b/548/DEPENDENCIES/6_16d_data.sci new file mode 100755 index 000000000..53529655f --- /dev/null +++ b/548/DEPENDENCIES/6_16d_data.sci @@ -0,0 +1,7 @@ +//for the jet power executive aircraft(CJ-1):
+S=29.54;//wingarea(m^2)
+D=1.225;//density at sea level(Kg/m^3)
+W=88176.75;//normal gross weight(N)
+Tf=16245;//thrust (N) provided by single turbofan engine
+Cdo=0.02;//parasite drag coefficient
+L_Dmax=16.9;//maximum L/D ,from example 6.13
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_17data.sci b/548/DEPENDENCIES/6_17data.sci new file mode 100755 index 000000000..c44970687 --- /dev/null +++ b/548/DEPENDENCIES/6_17data.sci @@ -0,0 +1,17 @@ +//for the jet power executive aircraft(CJ-1):
+W=88176.75;//normal gross weight(N)
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+e=0.81;//oswald efficiency factor
+h=1.83;//Height(m)of wing above ground
+D=1.225;//density at sea level(Kg/m^3)
+g=9.8;//Gravitational constant
+Ur=0.02;//Rolling friction coefficient
+Cl=1.0;//maximum lift coefficient during ground roll
+Cdo=0.02;//parasite drag coefficient
+T=32485;//thrust(N)
+phi=(16*h/b)^2/(1+(16*h/b)^2)//Ground effect factor
+Vlo=1.2*sqrt(2*W/(D*S*Cl))//liftoff velocity(1.2*Vstall in m/s)
+Dr=D*(0.7*Vlo)^2*S*(Cdo+phi*Cl^2/(%pi*e*AR))/2//drag(N)
+L=D*(0.7*Vlo)^2*S*Cl/2//lift(N)
diff --git a/548/DEPENDENCIES/6_18data.sci b/548/DEPENDENCIES/6_18data.sci new file mode 100755 index 000000000..d30937151 --- /dev/null +++ b/548/DEPENDENCIES/6_18data.sci @@ -0,0 +1,11 @@ +//for the CJ-1:
+W=54966.4;//empty weight(N)
+S=29.54;//wingarea(m^2)
+D=1.225;//density at sea level(Kg/m^3)
+g=9.8;//Gravitational constant
+Ur=0.4;//Rolling friction coefficient
+Clmax=2.5;//maximum lift coefficient
+Cd=0.02;//parasite drag coefficient
+Cdo=Cd+.1*Cd;//increase in parasite drag coefficient
+Vt=1.3*sqrt(2*W/(D*S*Clmax));//safe velocity(1.3*Vstall) during landing
+Dr=D*(0.7*Vt)^2*S*Cdo/2;//drag(N)
diff --git a/548/DEPENDENCIES/6_19data.sci b/548/DEPENDENCIES/6_19data.sci new file mode 100755 index 000000000..e01c5a8bb --- /dev/null +++ b/548/DEPENDENCIES/6_19data.sci @@ -0,0 +1,15 @@ +//for the cessna skylane(CP-1):
+W=11494.35;//fuel empty weight(N)
+W1=3916//total weight(N) including pilot seat etc
+Wf=1633.15;//weight(N) of fuel
+Wo=W+Wf-W1 //gross weight of UAV
+b=10.912;//wingspan(meter)
+S=16.16;//wingarea(m^2)
+AR=b^2/S//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+Pa=0.8*230*746 //maximum power available(J/s) from example 6.4
+//from example 6.12:
+n=0.8;
+c=7.45*10^-7;
diff --git a/548/DEPENDENCIES/6_1a_data.sci b/548/DEPENDENCIES/6_1a_data.sci new file mode 100755 index 000000000..386493996 --- /dev/null +++ b/548/DEPENDENCIES/6_1a_data.sci @@ -0,0 +1,14 @@ +//for the cessna skylane(CP-1):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=13127.5;//normal gross weight(N)
+f=65;//fuel capacity
+P=230;//power provided by piston engine (unit-horsepower(hp))
+Sf=2.0025;//specific fuel consumption(N/(hp.h))
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+Pf=0.8;//propeller efficiency
+V = linspace(30,400,500);//velocity over which we have to find thrust(30 to 400 m/s and over 500 points)
+
diff --git a/548/DEPENDENCIES/6_1b_data.sci b/548/DEPENDENCIES/6_1b_data.sci new file mode 100755 index 000000000..c265fdb50 --- /dev/null +++ b/548/DEPENDENCIES/6_1b_data.sci @@ -0,0 +1,14 @@ +//for the jet power executive aircraft(CJ-1):
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+W=88176.75;//normal gross weight(N)
+f=1119;//fuel capacity
+Tf=16245;//thrust (N) provided by single turbofan engine
+Sf=0.102;//specific fuel consumption(N/(hp.h))
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+V=linspace(40,300,500);//velocity over which we have to find thrust(40 to 300 m/s and over 500 points)
+
+
diff --git a/548/DEPENDENCIES/6_20data.sci b/548/DEPENDENCIES/6_20data.sci new file mode 100755 index 000000000..79ef090b2 --- /dev/null +++ b/548/DEPENDENCIES/6_20data.sci @@ -0,0 +1,2 @@ +n1=9;//maximum load factor for piloted airplane
+n2=25;//maximum load factor for UCAV
\ No newline at end of file diff --git a/548/DEPENDENCIES/6_3a_data.sci b/548/DEPENDENCIES/6_3a_data.sci new file mode 100755 index 000000000..9abe5b01f --- /dev/null +++ b/548/DEPENDENCIES/6_3a_data.sci @@ -0,0 +1,10 @@ +//for the cessna skylane(CP-1):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+Pf=0.8;//propeller efficiency
+V = linspace(20,400,500);//velocity over which we have to find Power(20 to 400 m/s and over 500 points)
+
diff --git a/548/DEPENDENCIES/6_3b_data.sci b/548/DEPENDENCIES/6_3b_data.sci new file mode 100755 index 000000000..c1c5bd3cd --- /dev/null +++ b/548/DEPENDENCIES/6_3b_data.sci @@ -0,0 +1,9 @@ +//for the jet power executive aircraft(CJ-1):
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=0.6107;//density at 6705.6 meter
+W=88176.75;//normal gross weight(N)
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+V=linspace(20,300,500);//velocity over which we have to find Power(20 to 300 m/s and over 500 points)
diff --git a/548/DEPENDENCIES/6_4a_data.sci b/548/DEPENDENCIES/6_4a_data.sci new file mode 100755 index 000000000..cd95827ef --- /dev/null +++ b/548/DEPENDENCIES/6_4a_data.sci @@ -0,0 +1,11 @@ +//for the CP-1(datas from example 6.1a):
+b=10.912;//wingspan(meter)
+S=16.165;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+D=1.225;//density at sea level(Kg/m^3)
+Cdo=0.025;//parasite drag coefficient
+e=0.8;//oswald efficiency factor
+W=13127.5;//normal gross weight(N)
+P=230;//power provided by piston engine (unit-horsepower(hp))
+Pf=0.8;//propeller efficiency
+Pa=P*Pf*746/1000//maximum power(KN-m/s),1hp=746 N-m/s
diff --git a/548/DEPENDENCIES/6_4b_data.sci b/548/DEPENDENCIES/6_4b_data.sci new file mode 100755 index 000000000..0f9234cfc --- /dev/null +++ b/548/DEPENDENCIES/6_4b_data.sci @@ -0,0 +1,12 @@ +//for the jet power executive aircraft(CJ-1):
+Tf=2*16245;//thrust (N) provided by both turbofan engine
+Do=1.225;//density(Kg/m^3) at sea level
+D=0.6107;//density(Kg/m^3) at height 6705.6 m
+b=16.25;//wingspan(meter)
+S=29.54;//wingarea(m^2)
+AR=b^2/S;//aspect ratio
+W=88176.75;//normal gross weight(N)
+Cdo=0.02;//parasite drag coefficient
+e=0.81;//oswald efficiency factor
+//in order to find max. velocity we need to find out the intersection of power required curve for example 6.3b and power available curve at height of 6705m:
+
diff --git a/548/DEPENDENCIES/7_02data.sci b/548/DEPENDENCIES/7_02data.sci new file mode 100755 index 000000000..9085b41e9 --- /dev/null +++ b/548/DEPENDENCIES/7_02data.sci @@ -0,0 +1,3 @@ +Clwb=0.45;//lift coefficient for wing body
+Cmac=-0.016;//moment coefficient about the aerodynamic center
+dh=0.05;//distance between aerodynamic center and center of gravity
\ No newline at end of file diff --git a/548/DEPENDENCIES/7_03data.sci b/548/DEPENDENCIES/7_03data.sci new file mode 100755 index 000000000..54c916971 --- /dev/null +++ b/548/DEPENDENCIES/7_03data.sci @@ -0,0 +1,12 @@ +h=0.35;//location of center of gravity from leading edge
+ao=-1.5;//geometric angle of attack for which lift is zero
+a1=5;//angle of attack in degree
+Cl1=0.52;//lift coefficient at 5 degree angle of attack
+Awb=(.52-0)/(5-(-1.5)) //lift slope per degree
+a2=1;//geometric angle of attack in degree
+ab2=a2+1.5//absolute angle of attack at 1 degree
+Cmcg=-0.01;//moment coefficient about center of gravity at 1 degree angle of attack
+a3=7.88;//geometric angle of attack in degree
+ab3=a3+1.5;//absolute angle of attack at 7.88 degree
+Cmcg2=0.05;//moment coefficient about center of gravity at 7.88 degree angle of attack
+//we have two equation in the form of Cmcg=Cmac+Clwb*(dh) and two unknown variables Cmac(moment coefficient about aerodynamic center )and dh(distance between aerodynamic center and center of gravity),so we use matrix method to solve them:
\ No newline at end of file diff --git a/548/DEPENDENCIES/7_04data.sci b/548/DEPENDENCIES/7_04data.sci new file mode 100755 index 000000000..ca2c461b7 --- /dev/null +++ b/548/DEPENDENCIES/7_04data.sci @@ -0,0 +1,15 @@ +//consider the wing model of example 7.3:
+S=0.1;//area of wing(m^2)
+c=0.1;//chord of wing(m)
+lt=0.17;//distance between airplane'scenter of gravity and aerodynamic center of tail
+St=0.02;//tail area(m^2)
+It=2.7;//tail settling area(degree)
+at=0.1;//tail lift slope per degree
+eo=0;//downwash angle at zero lift
+de=0.35;//derivative of downwash angle w.r.t angle of attack
+Vh=lt*St/(c*S)//tail volume ratio
+//following datas are from example 7.3
+Cmac=-0.032;//moment coefficient about the aerodynamic center
+a=0.08;//lift slope
+a1=7.88+1.5;//absolute angle of attack(degree)
+dh=0.11;//distance between aerodynamic center and center of gravity
\ No newline at end of file diff --git a/548/DEPENDENCIES/7_05data.sci b/548/DEPENDENCIES/7_05data.sci new file mode 100755 index 000000000..f8a2d65f7 --- /dev/null +++ b/548/DEPENDENCIES/7_05data.sci @@ -0,0 +1,18 @@ +//consider the wing-body-tail wind tunnel model of example 7.4.
+a=0.08;//lift slope
+S=0.1;//area of wing(m^2)
+c=0.1;//chord of wing(m)
+lt=0.17;//distance between airplane'scenter of gravity and aerodynamic center of tail
+St=0.02;//tail area(m^2)
+It=2.7;//tail settling area(degree)
+at=0.1;//tail lift slope per degree
+eo=0;//downwash angle at zero lift
+de=0.35;//derivative of downwash angle w.r.t angle of attack
+Vh=lt*St/(c*S)//tail volume ratio
+Cmac=-0.032;//moment coefficient about the aerodynamic center
+//derivative of Cmcg w.r.t absolute angle of attack:
+DCmcg=a*(dh-Vh*at*(1-de)/a)
+//value of moment coefficient at zero absolute angle of attack Cmo:
+Cmo=Cmac+Vh*at*(It+eo)
+//equilibrium angle of attack(from moment coefficient curve):
+Ae=Cmo/0.0133
\ No newline at end of file diff --git a/548/DEPENDENCIES/7_06data.sci b/548/DEPENDENCIES/7_06data.sci new file mode 100755 index 000000000..4044367a9 --- /dev/null +++ b/548/DEPENDENCIES/7_06data.sci @@ -0,0 +1,6 @@ +//consider wind tunnel model of example 7.3.datas are taken from example 7.3 and 7.4
+Hac=0.24;//distance of aerodynamic center from leading edge
+a=0.08;//lift slope
+Vh=lt*St/(c*S)//tail volume ratio
+at=0.1;//tail lift slope per degree
+de=0.35;//derivative of downwash angle w.r.t angle of attack
\ No newline at end of file diff --git a/548/DEPENDENCIES/7_07data.sci b/548/DEPENDENCIES/7_07data.sci new file mode 100755 index 000000000..14dd5a497 --- /dev/null +++ b/548/DEPENDENCIES/7_07data.sci @@ -0,0 +1,2 @@ +h=0.35;//location of center of gravity from leading edge
+Hn=0.516;//Neutral point location
diff --git a/548/DEPENDENCIES/7_08data.sci b/548/DEPENDENCIES/7_08data.sci new file mode 100755 index 000000000..b29698094 --- /dev/null +++ b/548/DEPENDENCIES/7_08data.sci @@ -0,0 +1,11 @@ +W=2.27*10^4;//weight of the airplane(N)
+S=19;//wing area (m^2)
+V=61;//velocity at sea level(m/s)
+D=1.225;//density at sea level(Kg/m^3)
+Cl=2*W/(D*S*V^2) //lift coefficient
+a=0.08;//lift slope per degree (from example 7.3)
+a1=Cl/a //absolute angle of attack
+DCmcg=-0.0133;//derivative of Cmcg w.r.t absolute angle of attack(from example 7.5)
+Cmo=0.06;//value of moment coefficient at zero absolute angle of attack (from example 7.5)
+Vh=0.34 //tail volume ratio(from example 7.4)
+DClt=0.04;//elevator control efficiency
diff --git a/548/DEPENDENCIES/7_09data.sci b/548/DEPENDENCIES/7_09data.sci new file mode 100755 index 000000000..cdbb812e1 --- /dev/null +++ b/548/DEPENDENCIES/7_09data.sci @@ -0,0 +1,11 @@ +//consider the airplane of example 7.8.its elevator hinge derivatives are:
+DCh=-0.008;//derivative w.r.t absolute angle of attack of tail
+DChe=-0.013;//derivative w.r.t elevator deflection
+at=0.1;//tail lift slope per degree(from example 7.4)
+DClt=0.04;// elevator control efficiency (from example 7.8)
+Hac=0.24;//location of aerodynamic center from leading edge(from example 7.3)
+Vh=0.34;//tail volume ratio(from example 7.4)
+de=0.35;//derivative of downwash angle w.r.t angle of attack(from example 7.4)
+a=0.08;//lift slope(from example 7.4)
+F=1-DClt*DCh/(at*DChe) //free elevator factor
+Hn=Hac+F*Vh*at*(1-de)/a //neutral point
diff --git a/548/DEPENDENCIES/8_01data.sci b/548/DEPENDENCIES/8_01data.sci new file mode 100755 index 000000000..26068ebff --- /dev/null +++ b/548/DEPENDENCIES/8_01data.sci @@ -0,0 +1,7 @@ +V=9000;//burnout velocity(m/s)
+alpha=3*%pi/180;//direction of bernout velocity due north above local horizontal(degree)
+H=.805*10^6;//altitude above sea level(meter)
+beeta=27*%pi/180;//angle made by burnout point with equator
+Re=6.4*10^6;//radius(m)of earth
+Rb=7.2*10^6 //distance of bernout point from earth's center
+K=3.986*10^14;//product of earth's mass and universal Gravitational constant.
diff --git a/548/DEPENDENCIES/8_02data.sci b/548/DEPENDENCIES/8_02data.sci new file mode 100755 index 000000000..24b77cbba --- /dev/null +++ b/548/DEPENDENCIES/8_02data.sci @@ -0,0 +1,3 @@ +T1=365.256;//period of revolution of earth around sun(days)
+a1=1.49527*10^11;//semimajor axis of earth's orbit(m)
+a2=2.2783*10^11;//semimajor axis of Mars's orbit(m)
\ No newline at end of file diff --git a/548/DEPENDENCIES/8_03data.sci b/548/DEPENDENCIES/8_03data.sci new file mode 100755 index 000000000..7af25b59c --- /dev/null +++ b/548/DEPENDENCIES/8_03data.sci @@ -0,0 +1,12 @@ +Ve=13000;//velocity of solid iron sphere entering earth's atmosphere(m/s)
+theta=15*%pi/180 //angle at which sphere is entering
+r=0.5;//sphere radius(m)
+Cd=1;//drag coefficient for a sphere at hypersonic speed
+Ds=6963;//density of sphere(Kg/m^3)
+g=9.8;//gravitational constant(m/s^2)
+R=287;//gas constant for air(J/Kg.K)
+Do=1.225;//density at sea level(Kg/m^3)
+T=288;//assuming a constant temperature(k) for exponential universe
+B=4*r*Ds/(3*Cd) //ballistic parameter(m/CD*S=4*r*Ds/(3*Cd))
+Z=.000118
+D=B*Z*sin(theta) //density at corresponding altitude of maximum deceleration
\ No newline at end of file diff --git a/548/DEPENDENCIES/9_01data.sci b/548/DEPENDENCIES/9_01data.sci new file mode 100755 index 000000000..72941f043 --- /dev/null +++ b/548/DEPENDENCIES/9_01data.sci @@ -0,0 +1,20 @@ +//consider a six cylinder internal combustion engine.
+y=1.4;//specific heat ratio for air
+Stroke=9.5;//stroke (cm)of the internal combustion engine
+b=9;//bore(cm)of the internal combustion engine
+P2=0.8*1.01*10^5;//pressure (N/m^2)before compression stroke
+T2=250;//temperature(k) before compression stroke
+//V2 and V3 are volume before and after compression stroke respectively and V4 and V5 volume before and after power stroke respectively.
+r=10;//compression ratio(V2/V3)
+f=0.06;//fuel to air ratio by mass
+P3=P2*r^y //pressure after compression stroke(isentropic condition)
+T3=T2*r^(y-1)//temperature after compression stroke
+//chemical energy released in 1 Kg gasoline is 4.29*10^7 Joule so,heat released per Kg of fuel air mixture q equals:
+q=4.29*10^7*0.06/1.06
+Cv=720;//specific heat ratio(J/Kg-K)at constant volume for air
+T4=q/Cv+T3 //temperature before power stroke
+P4=P3*T4/T3 //pressure before power stroke
+P5=P4*(1/r)^y //pressure after power stroke from isentropic relation
+n=0.83;//propeller efficiency
+nm=0.75;//mechanical efficiency
+rpm=3000;//rotation per minute for the engine
diff --git a/548/DEPENDENCIES/9_02data.sci b/548/DEPENDENCIES/9_02data.sci new file mode 100755 index 000000000..9a3c3ed5d --- /dev/null +++ b/548/DEPENDENCIES/9_02data.sci @@ -0,0 +1,11 @@ +//consider the engine of example 9.1,datas are same as 9.1
+Pa=1.034*10^4;//total power available(N/m^2)
+n=0.83;//propeller efficiency
+Nmech=0.75;//mechanical efficiency
+rpm=3000;//for engine-propeller combination(revolution per minute)
+b=9*10^-2;//bore(meter)
+s=9.5*10^-2;//engine stroke
+N=6;//number of cylinders
+d=%pi*b^2*s*N/4 //displacement(meter)
+
+
\ No newline at end of file diff --git a/548/DEPENDENCIES/9_03data.sci b/548/DEPENDENCIES/9_03data.sci new file mode 100755 index 000000000..948b55d28 --- /dev/null +++ b/548/DEPENDENCIES/9_03data.sci @@ -0,0 +1,9 @@ +H=9144;//standard altitude at which airplane flying(meter)
+P=0.3014*10^5;//pressure at standard altitude of 9144 m(N/m^2)
+D=0.459;//Density at standard altitude of 9144 m(Kg/m^3)
+V=804.67*5/18 //free stream velocity(m/s)
+Pe=0.3064*10^5;//pressure of exhaust gas at the exit(N/m^2)
+Ve=487.68;//velocity of exhaust gas at exit(m/s)
+Ai=0.65;//inlet area(m^2)
+Ae=0.42;//exit area(m^2)
+Mdot=D*V*Ai //mass flow through engine(Kg/s)
diff --git a/548/DEPENDENCIES/9_04data.sci b/548/DEPENDENCIES/9_04data.sci new file mode 100755 index 000000000..5dc55e0a7 --- /dev/null +++ b/548/DEPENDENCIES/9_04data.sci @@ -0,0 +1,19 @@ +//consider a rocket engine burning hydrogen and oxygen.
+Po=25*1.01*10^5;//pressure at combustion chamber(N/m^2)
+To=3517;//temperature of combustion chamber(K)
+A=0.1;//area of rocket nozzle(m^2)
+Pe=1.1855*10^3;//exit pressure(N/m^2) at standard altitude of 30 Km
+y=1.22;//specific heat ratio of the gas mixture
+g=9.8;
+M=16;//Molecular weight of gas mixture
+Ru=8314;//universal gas constant(J/Kg.K)
+R=8314/16 //specicific gas constant for this mixture
+//specific impulse Isp:
+Isp=sqrt(2*y*Ru*To*[1-(Pe/Po)^((y-1)/y)]/((y-1)*M))/g
+//mass flow through engine(Kg/s):
+Mdot=(Po*A/sqrt(To))*sqrt(y*(2/(y+1))^((y+1)/(y-1)) /R)
+Te=To*(Pe/Po)^((y-1)/y) //exit temperature in Kelvin
+Cp=y*R/(y-1) //specific heat at constant pressure for the gas mixture
+Ve=sqrt(2*Cp*(To-Te)) //velocity at exit of exhaust gas(m/s)
+De=Pe/(R*Te) //exit density(Kg/m^3)
+
diff --git a/548/DEPENDENCIES/9_05data.sci b/548/DEPENDENCIES/9_05data.sci new file mode 100755 index 000000000..a1afc814b --- /dev/null +++ b/548/DEPENDENCIES/9_05data.sci @@ -0,0 +1,24 @@ +Mt=5000;//total mass(Kg) for both the rocket
+Isp=350;//specific impulse (s)for both rocket
+g=9.8;
+//for the single stage rocket:
+Ms=500;//structural mass(Kg)
+Mp=4450;//propellent mass(Kg)
+Ml=50;//payload mass(Kg)
+Mi=Ms+Mp+Ml;//initial mas(Kg)
+Mf=Ms+Ml;//final mass(Kg)
+Vb=g*Isp*log(Mi/Mf)//burnout velocity(m/s)
+//for the double-stage Rocket
+Ms1=400;//structural mass (Kg)of first stage
+Mp1=3450;//propellent mass(Kg)of first stage
+Ms2=100;//structural mass (Kg)of second stage
+Mp2=1000;//propellent mass(Kg)of second stage
+Ml=50;//payload mass(Kg)
+Mi2=Ms1+Mp1+Ms2+Mp2+Ml;//initial mas(Kg)
+Mf2=Ms1+Ms2+Ml;//final mass(Kg)
+//burnout velocity(m/s) of the first stage:
+Vb1=g*Isp*log((Mp1+Ms1+Mp2+Ms2+Ml)/(Ms1+Mp2+Ms2+Ml))
+//increase in velocity by second stage DVb:
+DVb=g*Isp*log((Mp2+Ms2+Ml)/(Ms2+Ml))
+//velocity at burnout of second stage
+Vb2=Vb1+DVb
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