diff options
Diffstat (limited to '689')
75 files changed, 1451 insertions, 0 deletions
diff --git a/689/CH10/EX10.1/1.sce b/689/CH10/EX10.1/1.sce new file mode 100644 index 000000000..b1d78f684 --- /dev/null +++ b/689/CH10/EX10.1/1.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 10.1 Induced Drag
+
+// Initialisation of variables
+S = 39;
+C = 6;
+Cl = 0.8;
+
+// Calculations
+AR = S/C;
+alpha_i = 18.24*Cl/AR;
+Cd_i = Cl^2/(%pi*AR);
+
+//Results
+disp(Cd_i,"Induced drag coefficient :", alpha_i, "Induced angle of attack (degree) :");
\ No newline at end of file diff --git a/689/CH10/EX10.10/10.sce b/689/CH10/EX10.10/10.sce new file mode 100644 index 000000000..19bfc2bda --- /dev/null +++ b/689/CH10/EX10.10/10.sce @@ -0,0 +1,33 @@ +clc; funcprot(0);
+//Example 10.10 Ground Effect
+
+// Initialisation of variables
+alp = 10; //True angle of attack
+c = 6;
+b = 36;
+V = 100; // Free stream velocity
+rho = 0.002387;
+Cl = 1.07; //From fig 8.8
+Cd = 0.077; //From fig 8.8
+z = 4; // Height above ground
+gap = 2*z;
+
+// Calculations
+S = c*b;
+L = Cl*(rho/2)*S*V^2;
+D = Cd*(rho/2)*S*V^2;
+gapBYspan = gap/S;
+sigma = 0.46; // From fig 8.10
+EMAR = (b^2/S)/(1-sigma);
+alpG = alp - (-5); //Effective geometric angle of attack for clark Y after sutracting zero lift angle.
+a = alpG - 18.25*(1/c -1/EMAR) //Angle of attack measured from angle of zero lift for Cl = 1.07.
+m = Cl/a; // Slope of lift curve
+Cl_g = alpG*m // Lift Coefficient taking ground under consideration
+L_g = Cl_g*(rho/2)*S*V^2 ; //Lift taking ground under consideration
+Cd = 0.090; //From figure 8.8 for Cl = 1.19
+Cd_g = Cd - (Cl^2/%pi)*(1/c -1/EMAR); // Lift Coefficient taking ground under consideration
+D_g = Cd_g*(rho/2)*S*V^2 ; //Drag taking ground under consideration
+
+//Results
+disp(D,"Drag when ground is neglected (lb) :", L,"Lift when ground is neglected (lb) :" );
+disp(D_g,"Drag when ground is considered (lb) :", L_g,"Lift when ground is considered (lb) :" );
diff --git a/689/CH10/EX10.2/2.sce b/689/CH10/EX10.2/2.sce new file mode 100644 index 000000000..0963a4df7 --- /dev/null +++ b/689/CH10/EX10.2/2.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 10.2 Horse Power Required for Induce Drag
+
+// Initialisation of variables
+W = 2000;
+b = 38;
+alt = 10000;
+V = 80*1.467;
+
+// Calculations
+Di = (363*(W/b)^2)/V^2
+HP_Di = Di*V/550;
+
+//Results
+disp(HP_Di,"Horse power required to overcome induced drag (HP) :");
\ No newline at end of file diff --git a/689/CH10/EX10.3/3.sce b/689/CH10/EX10.3/3.sce new file mode 100644 index 000000000..eff54bf58 --- /dev/null +++ b/689/CH10/EX10.3/3.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 10.3 Correction for aspect ratio of monoplane
+
+// Initialisation of variables
+AR6 = 6;
+alp6 = 3;
+Cl = 0.381;
+Cd6 = 0.0170;
+AR4 = 4;
+
+// Calculations
+alp4 = alp6 - 18.24*Cl*(1/AR6 - 1/AR4);
+Cd4 = Cd6 - Cl^2*(1/%pi)*(1/AR6 - 1/AR4);
+
+//Results
+disp(Cd4,"Drag Coefficient at aspect ratio 4 :", alp4,"Angle of attack for aspect ration 4 :" );
\ No newline at end of file diff --git a/689/CH10/EX10.4/4.sce b/689/CH10/EX10.4/4.sce new file mode 100644 index 000000000..7b0e9e14a --- /dev/null +++ b/689/CH10/EX10.4/4.sce @@ -0,0 +1,18 @@ +clc; funcprot(0);
+//Example 10.4 Coefficient for infinite aspect ratio
+
+// Initialisation of variables
+Cl0 = 1.03;
+alp0 = 9;
+Cd0 = 0.067;
+Cl8 = 1.03;
+AR8 = 8;
+
+// Calculations
+alpi = 18.24*Cl0/AR8
+Cdi = Cl0^2/(%pi*AR8)
+alp = alp0 +alpi;
+Cd =Cd0 +Cdi;
+
+//Results
+disp(Cd,"Drag Coefficient at aspect ratio 8 :", alp,"Angle of attack for aspect ratio 8 (Degree):" );
\ No newline at end of file diff --git a/689/CH10/EX10.5/5.sce b/689/CH10/EX10.5/5.sce new file mode 100644 index 000000000..9e57ece06 --- /dev/null +++ b/689/CH10/EX10.5/5.sce @@ -0,0 +1,13 @@ +clc; funcprot(0);
+//Example 10.5 Coefficient for infinite aspect ratio
+
+// Initialisation of variables
+slope = 0.09;
+alp = 9;
+AR = 6;
+
+// Calculations
+Cl = alp*slope/(1 + 18.24*slope/AR);
+
+//Results
+disp(Cl,"Lift Coefficient for AR = 6 and alpha = 9 :" );
\ No newline at end of file diff --git a/689/CH10/EX10.6/6.sce b/689/CH10/EX10.6/6.sce new file mode 100644 index 000000000..bb4f07173 --- /dev/null +++ b/689/CH10/EX10.6/6.sce @@ -0,0 +1,26 @@ +clc; funcprot(0);
+//Example 10.6 Induced drag of tappered wings
+
+// Initialisation of variables
+b = 46;
+w = 4;
+c = 8;
+r = 2;
+//data from figure 10.9
+CO = sqrt(6^2+19^2);
+CH = sqrt(19.93^2 - 2^2);
+EOH = atand(6/19);
+COH = acosd(2/19.93);
+GOH = 270 - EOH - COH;
+Area_ABCD = 2*c;
+Area_BGOC = 19*(2+8)*0.5;
+Area_COH = 0.5*r*CH;
+Area_GOH = GOH/360*(%pi*r^2);
+
+// Calculations
+Area_half_wing = Area_ABCD + Area_BGOC + Area_COH + Area_GOH;
+S = 2*Area_half_wing;
+AR = b^2/S;
+
+//Results
+disp(AR,"Required aspect ratio :" );
diff --git a/689/CH10/EX10.7/7.sce b/689/CH10/EX10.7/7.sce new file mode 100644 index 000000000..e9a57d3ff --- /dev/null +++ b/689/CH10/EX10.7/7.sce @@ -0,0 +1,22 @@ +clc; funcprot(0);
+//Example 10.7 Equivalent monoplane aspect ratio
+
+// Initialisation of variables
+b1 = 40;
+C1 = 4+10/12;
+b2 = 32;
+C2 = 3+9/12;
+gap = 4.5;
+
+// Calculations
+mu = b2/b1;
+Ratio_Gap_to_mean_span = 2*gap/(b1+b2);
+sigma = 0.56; //From figure 10.10
+A1 = b1*C1;
+A2 = b2*C2;
+S = A1+A2;
+r = A2/A1;
+EMAR = (b1^2/S)*(mu*(1+r))^2/(mu^2 + 2*sigma*mu*r + r^2) ;
+
+//Results
+disp(EMAR,"Effective monoplane aspect ratio :" );
\ No newline at end of file diff --git a/689/CH10/EX10.8/8.sce b/689/CH10/EX10.8/8.sce new file mode 100644 index 000000000..1f278ab2d --- /dev/null +++ b/689/CH10/EX10.8/8.sce @@ -0,0 +1,22 @@ +clc; funcprot(0);
+//Example 10.8 Best lift distribution in biplane
+
+// Initialisation of variables
+b1 = 30;
+b2 = 27;
+gap = 4.5;
+S = 400;
+
+// Calculations
+mu = b2/b1;
+gapBYmeanspan = 2*gap/(b1+b2);
+sigma = 0.538; //From fig 10.10
+r = (mu^2-sigma*mu)/(1-sigma*mu);
+S1 = r*S;
+S2 = S - S1;
+C1 = S1/b1;
+C2 = S2/b2;
+EMAR = (b1^2/S)*(1 - 2*sigma*mu + mu^2)/(1-sigma^2) ;
+
+//Results
+disp(EMAR,"EMAR when total area is 400 sq-ft :",r, "Ratio of areas of lower to upper wing " );
\ No newline at end of file diff --git a/689/CH10/EX10.9/9.sce b/689/CH10/EX10.9/9.sce new file mode 100644 index 000000000..a5cba1c37 --- /dev/null +++ b/689/CH10/EX10.9/9.sce @@ -0,0 +1,20 @@ +clc; funcprot(0);
+//Example 10.9 Equivalent monoplane span
+
+// Initialisation of variables
+b1 = 32;
+b2 = 29;
+gap = 4.63;
+S1 = 152;
+S2 = 120;
+
+// Calculations
+mu = b2/b1;
+gapBYmeanspan = 2*gap/(b1+b2);
+sigma = 0.54; // from fig 10.10
+r = S2/S1;
+k = sqrt(mu^2*(1+r)^2)/sqrt(mu^2 + 2*sigma*r*mu + r^2);
+kb1 = k*b1;
+
+//Results
+disp(kb1,"Equivalent monoplane span (ft):" );
\ No newline at end of file diff --git a/689/CH10/EX11.2/2.sce b/689/CH10/EX11.2/2.sce new file mode 100644 index 000000000..3366f3ce6 --- /dev/null +++ b/689/CH10/EX11.2/2.sce @@ -0,0 +1,21 @@ +clc; funcprot(0);
+//Example 11.2 Critical Pressure
+
+// Initialisation of variables
+V0 = 1.689*500; //Velocity in ft/sec
+rho = 0.001267; //From table 4.1
+P = (848.7/12)*13.75; // Pressure at 20,000 ft
+gma = 1.4;
+g = 32.174;
+R = 53.351;
+T = 459.4+25; //Temperature in Rankine
+
+// Calculations
+a0 = sqrt(gma*g*R*T);
+M0 = V0/a0;
+Pcr = (2/gma/M0^2)*((2/(gma + 1)+ (gma-1)*M0^2/(gma+1))^(gma/(gma-1))-1);
+
+
+
+//Results
+disp(Pcr,"Critical Pressure Coefficient: ") ;
diff --git a/689/CH11/EX11.1/1.sce b/689/CH11/EX11.1/1.sce new file mode 100644 index 000000000..414dbfbfb --- /dev/null +++ b/689/CH11/EX11.1/1.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 11.1 Critical Velocity
+
+// Initialisation of variables
+V0 = 1.47*480; //Velocity in ft/sec
+rho = 0.001267; //From table 4.1
+P = (848.7/12)*13.75; // Pressure at 20,000 ft
+gma = 1.4;
+
+// Calculations
+a0 = sqrt(gma*P/rho);
+M0 = V0/a0;
+Vcr = a0*sqrt(((gma - 1)*M0^2 + 2)/(gma+1));
+
+//Results
+disp(Vcr/1.467,"Critical velocity(mph): ") ;
diff --git a/689/CH11/EX11.3/3.sce b/689/CH11/EX11.3/3.sce new file mode 100644 index 000000000..fef0b6a7e --- /dev/null +++ b/689/CH11/EX11.3/3.sce @@ -0,0 +1,26 @@ +clc; funcprot(0);
+//Example 11.3 Lift at subsonic speed
+
+// Initialisation of variables
+alp_z = -4; //Angle of attack at zero lift
+M16 = 0.16;
+Cl = 0.3;
+alp = 1.5;
+M0 = 0;
+M65 = 0.65;
+alp25 = 2.5;
+
+// Calculations
+//At M = 1.6
+DCl_by_Dalp16 = Cl/(alp-alp_z);
+
+//At M = 0
+DCl_by_Dalp0 = DCl_by_Dalp16*sqrt(1-M16^2);
+
+////At M = 0.65
+DCl_by_Dalp65 = DCl_by_Dalp0/sqrt(1-M65^2);
+
+Cl25 = (alp25 - alp_z)*DCl_by_Dalp65;
+
+//Results
+disp(Cl25,"Lift Coefficient at alpha = 2.5 degree: ") ;
diff --git a/689/CH13/EX13.1/1.sce b/689/CH13/EX13.1/1.sce new file mode 100644 index 000000000..d6524c220 --- /dev/null +++ b/689/CH13/EX13.1/1.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 13.1 Struts
+
+// Initialisation of variables
+V = 100;
+l = 6;
+n = 4;
+D_rnd = 3/4;
+D_stln = 5/8;
+
+// Calculations
+Drag_rnd = 0.00026*D_rnd*V^2*l*n;
+Drag_stln = 0.0000175*D_stln*V^2*l*n;
+
+//Results
+disp(Drag_stln,"Drag due to streamlined struts(lb) :", Drag_rnd, "Drag due to round struts(lb) :");
diff --git a/689/CH15/EX15.1/1.sce b/689/CH15/EX15.1/1.sce new file mode 100644 index 000000000..cd43d9e3f --- /dev/null +++ b/689/CH15/EX15.1/1.sce @@ -0,0 +1,20 @@ +clc; funcprot(0);
+//Example 15.1 Thrust and power coefficients
+
+// Initialisation of variables
+P = 500*550; // Power in ft-lb/sec
+V = 180*1.467; // Velocity in ft/sec
+n = 1900/60; // Rotaion per second
+D = 9; // Diameter in ft
+rho = 0.001756;
+
+
+// Calculations
+Cp = P/(rho*n^3*D^5);
+V_By_nD = V/(n*D);
+Ct = 0.074; // For corrosponding Cp and V/nD from figure 15.3.3
+T = Ct*rho*n^2*D^4;
+Eff = Ct*V_By_nD/Cp;
+
+//Results
+disp(Eff*100,"Propeller Efficiency (%) : ",T,"Thrust (lb) :") ;
diff --git a/689/CH15/EX15.2/2.sce b/689/CH15/EX15.2/2.sce new file mode 100644 index 000000000..1e673dd59 --- /dev/null +++ b/689/CH15/EX15.2/2.sce @@ -0,0 +1,32 @@ +clc; funcprot(0);
+//Example 15.2 Thrust of a fixed pitch propeller
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 2200/60; // Rotaion per second
+D = 6; // Diameter in ft
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+VnD0 = V/(n*D);
+Ct0 = 0.075;
+Cp0 = 0.076;
+T0 = Ct0*rho*n^2*D^4;
+
+V = [VnD0 0.6 0.5 0.4 0.3 0.2 0.1 0];
+Ct = [Ct0 0.120 0.132 0.144 0.160 0.173 0.186 0.198];
+Cp = [Cp0 0.103 0.108 0.112 0.118 0.122 0.124 0.127];
+CtByCp = diag(Ct)/diag(Cp);
+T = T0*(Cp0/Ct0)*CtByCp;
+Eff = diag(V)*diag(CtByCp);
+Result = zeros(8,6);
+Result(:,1) = V';
+Result(:,2) = Ct';
+Result(:,3) = Cp';
+Result(:,4) = diag(CtByCp);
+Result(:,5) = diag(T);
+Result(:,6) = Eff;
+
+//Results
+
+disp(Result,"!! V/nD Ct Cp Ct/Cp T Efficiency !!") ;
diff --git a/689/CH15/EX15.3/3.sce b/689/CH15/EX15.3/3.sce new file mode 100644 index 000000000..d69d98486 --- /dev/null +++ b/689/CH15/EX15.3/3.sce @@ -0,0 +1,47 @@ +clc; funcprot(0);
+//Example 15.3 Power of a fixed pitch propeller
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 2200/60; // Rotaion per second
+D = 6; // Diameter in ft
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+VnD0 = V/(n*D);
+Ct0 = 0.075;
+Cp0 = 0.076;
+T0 = Ct0*rho*n^2*D^4;
+
+V = [VnD0 0.8 0.7 0.6 0.5 0.4 ];
+Ct = [Ct0 0.082 0.100 0.120 0.132 0.144 ];
+Cp = [Cp0 0.080 0.093 0.103 0.108 0.112 ];
+CtByCp = diag(Ct)/diag(Cp);
+T = T0*(Cp0/Ct0)*CtByCp;
+Eff = diag(V)*diag(CtByCp);
+Eff0 = Eff(1);
+Cp0 = linspace(Cp0,Cp0, 6);
+Cp0ByCp = diag(diag(Cp0)/diag(Cp))
+
+Eff/Eff0;
+Eff/Eff0*(n*60);
+bhp = [125 123 117 112 110 109]; // From manufactures chart
+thp = diag(bhp)*diag(Eff);
+
+Result = zeros(6,11);
+Result(:,1) = V';
+Result(:,2) = Ct';
+Result(:,3) = Cp';
+Result(:,4) = Cp0ByCp;
+Result(:,5) = Eff/Eff0;
+Result(:,6) = Result(:,5)*2200;
+Result(:,7) = bhp';
+Result(:,8) = diag(CtByCp);
+Result(:,9) = Eff;
+Result(:,10) = diag(thp);
+Result(:,11) = diag(diag(Result(:,1))*diag(Result(:,6))*(D/88));
+
+//Results
+
+disp(Result,"!! V/nD Ct Cp CP0/Cp n/n0 rpm bhp Ct/Cp Efficiency thp V !!") ;
+disp("There is a calculation mistake in calculating n/no hence the dependent answer varies");
diff --git a/689/CH15/EX15.4/4.sce b/689/CH15/EX15.4/4.sce new file mode 100644 index 000000000..5361d7386 --- /dev/null +++ b/689/CH15/EX15.4/4.sce @@ -0,0 +1,49 @@ +clc; funcprot(0);
+//Example 15.4 Thrust Horse Power for a fixed pitch propeller
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 2200/60; // Rotaion per second
+D = 6; // Diameter in ft
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+VnD0 = V/(n*D);
+Ct0 = 0.075;
+Cp0 = 0.076;
+T0 = Ct0*rho*n^2*D^4;
+
+V = [VnD0 0.8 0.7 0.6 0.5 0.4 ];
+Ct = [Ct0 0.082 0.100 0.120 0.132 0.144 ];
+Cp = [Cp0 0.080 0.093 0.103 0.108 0.112 ];
+CtByCp = diag(Ct)/diag(Cp);
+T = T0*(Cp0/Ct0)*CtByCp;
+Eff = diag(V)*diag(CtByCp);
+Eff0 = Eff(1);
+RPM = Eff/Eff0*2200;
+Cp0 = linspace(Cp0,Cp0, 6);
+Cp0ByCp = diag(diag(Cp0)/diag(Cp))
+
+Eff/Eff0;
+Eff/Eff0*(n*60);
+bhp = [125 123 117 112 110 109]; // From manufactures chart
+thp = diag(bhp)*diag(Eff);
+sigma = 0.7384; // From table 4.1;
+Bhp10KBySL = 0.673; // Ratios of BHP from fig 14.3
+RPMfactor = Bhp10KBySL/sigma;
+BHPfactor = RPMfactor*Bhp10KBySL;
+
+Result = zeros(6,9);
+Result(:,1) = V';
+Result(:,2) = RPM;
+Result(:,3) = bhp';
+Result(:,4) = diag(diag(Result(:,1))*diag(Result(:,2))*(D/88));
+Result(:,5) = Eff;
+Result(:,6) = RPM*RPMfactor;
+Result(:,7) = bhp'*BHPfactor;
+Result(:,8) = Result(:,4)*RPMfactor;
+Result(:,9) = diag(diag(Result(:,7))*diag(Result(:,5)));
+//Results
+
+disp(Result,"!! V/nD rpm_SL bhp_SL V_SL Eff_SL rpm_10K bhp_10K V_10K thp_10K !!") ;
+disp("There is a calculation mistake in calculating n/no hence the dependent answer varies");
diff --git a/689/CH15/EX15.5/5.sce b/689/CH15/EX15.5/5.sce new file mode 100644 index 000000000..3c7ad9a4b --- /dev/null +++ b/689/CH15/EX15.5/5.sce @@ -0,0 +1,28 @@ +clc; funcprot(0);
+//Example 15.5 Thrust of a constant speed propeller
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 1800/60; // Rotaion per second
+D = 9.5; // Diameter in ft
+P = 600*550;
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+Cp = P/(rho*n^3*D^5);
+ThrustCoeff = rho*n^2*D^4;
+VeloCoeff = n*60*D/88;
+5
+VBynD = linspace(0.5,0,6);
+Ct = [0.09 0.101 0.112 0.122 0.132 0.142]; // From figure 15.4 for corrospondiong values of V/nD at Cp = 0.066
+T = Ct*ThrustCoeff;
+V = VBynD*VeloCoeff;
+
+Result = zeros(6,4);
+Result(:,1) = VBynD';
+Result(:,2) = Ct';
+Result(:,3) = T';
+Result(:,4) = V';
+//Results
+
+disp(Result,"!! V/nD Ct T V(mph) !!") ;
diff --git a/689/CH15/EX15.6/6.sce b/689/CH15/EX15.6/6.sce new file mode 100644 index 000000000..7362b8662 --- /dev/null +++ b/689/CH15/EX15.6/6.sce @@ -0,0 +1,30 @@ +clc; funcprot(0);
+//Example 15.6 Thrust Horsepower of a constant speed propeller at Sea level
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 1800/60; // Rotaion per second
+D = 9.5; // Diameter in ft
+P = 600*550;
+rho = 0.002378;
+
+// Calculations
+//For Beta = 23 degree
+Cp = P/(rho*n^3*D^5);
+ThrustCoeff = rho*n^2*D^4;
+VeloCoeff = n*60*D/88;
+
+VBynD = [1.03 1 0.9 0.8 0.7 0.6];
+Ct = [0.055 0.056 0.062 0.068 0.076 0.086]; // From figure 15.4 for corrospondiong values of V/nD at Cp = 0.066
+T = Ct*ThrustCoeff;
+V = VBynD*VeloCoeff;
+
+Result = zeros(6,6);
+Result(:,1) = VBynD';
+Result(:,2) = Ct';
+Result(:,3) = Result(:,2)/Cp;
+Result(:,4) = diag(diag(Result(:,3))*diag(Result(:,1))); // Using equation 15.5.5
+Result(:,5) = Result(:,4)*P/550;
+Result(:,6) = V';
+//Results
+
+disp(Result,"!! V/nD Ct Ct/Cp Efficiency thp V(mph) !!") ;
diff --git a/689/CH15/EX15.7/7.sce b/689/CH15/EX15.7/7.sce new file mode 100644 index 000000000..3dc23480d --- /dev/null +++ b/689/CH15/EX15.7/7.sce @@ -0,0 +1,30 @@ +clc; funcprot(0);
+//Example 15.7 Thrust Horsepower of a constant speed propeller at an altitude
+// Initialisation of variables
+V = 125*1.467; // Velocity in ft/sec
+n = 1800/60; // Rotaion per second
+D = 9.5; // Diameter in ft
+P = 600*550;
+rho = 0.001756;
+
+// Calculations
+//For Beta = 23 degree
+Cp = P/(rho*n^3*D^5);
+ThrustCoeff = rho*n^2*D^4;
+VeloCoeff = n*60*D/88;
+
+VBynD = [1 0.9 0.8 0.7 0.6];
+Ct = [0.073 0.081 0.087 0.096 0.108]; // From figure 15.4 for corrospondiong values of V/nD at Cp = 0.066
+T = Ct*ThrustCoeff;
+V = VBynD*VeloCoeff;
+
+Result = zeros(5,6);
+Result(:,1) = VBynD';
+Result(:,2) = Ct';
+Result(:,3) = Result(:,2)/Cp;
+Result(:,4) = diag(diag(Result(:,3))*diag(Result(:,1))); // Using equation 15.5.5
+Result(:,5) = Result(:,4)*P/550;
+Result(:,6) = V';
+//Results
+
+disp(Result,"!! V/nD Ct Ct/Cp Efficiency thp V(mph) !!") ;
diff --git a/689/CH16/EX16.1/1.pdf b/689/CH16/EX16.1/1.pdf Binary files differnew file mode 100644 index 000000000..25d86c55f --- /dev/null +++ b/689/CH16/EX16.1/1.pdf diff --git a/689/CH16/EX16.1/1.sce b/689/CH16/EX16.1/1.sce new file mode 100644 index 000000000..e4aaee889 --- /dev/null +++ b/689/CH16/EX16.1/1.sce @@ -0,0 +1,39 @@ +clc; funcprot(0);
+//Example 16.1 Horsepower required at sea level
+// Initialisation of variables
+W = 2000;
+b = 36;
+c = 6;
+Dp = 3.8; // Parasite drag equivalent
+
+// Calculations
+S = b*c;
+WingLoading = W/S;
+VeloCoeff = sqrt(WingLoading/0.00256)
+Hp_WingCoeff = 0.00256*S/375;
+Hp_parCoeff = 0.00327*Dp/375;
+
+alp = [-4 -3 -2 -1 0 4 8 12 16 18 19 20];
+Cl = [0.07 0.14 0.215 0.285 0.36 0.6455 0.93 1.19 1.435 1.545 1.560 1.540]; // Values from fig 8.8
+Cd = [0.010 0.010 0.012 0.014 0.017 0.033 0.060 0.095 0.139 0.164 0.180 0.206]; // Values from fig 8.8
+
+
+Result = zeros(12,7);
+Result(:,1) = alp';
+Result(:,2) = Cl';
+Result(:,3) = Cd';
+Result(:,4) = 60.0*diag(inv(diag(sqrt(Cl)'))); // Using equation 15.5.5
+Result(:,5) = diag(diag(Result(:,3))*diag(Result(:,4)^3))*Hp_WingCoeff;
+Result(:,6) = Result(:,4)^3*Hp_parCoeff;
+Result(:,7) = Result(:,5) + Result(:,6);
+
+//Results
+disp(Result,"!! alpha Cl Cd V HP wing HP Par HP Total !!") ;
+clf();
+plot2d(Result(:,4),[Result(:,5) Result(:,6) Result(:,7)]);
+legend(['HP Req Wing'; 'HP Req Par'; 'HP Req Total'],2);
+xlabel("Miles Per Hour");
+ylabel("HorsePower");
+title("Horsepower required for various airspeeds ");
+set(gca(),"grid",[1 1])
+
diff --git a/689/CH16/EX16.2/2.pdf b/689/CH16/EX16.2/2.pdf Binary files differnew file mode 100644 index 000000000..fce023575 --- /dev/null +++ b/689/CH16/EX16.2/2.pdf diff --git a/689/CH16/EX16.2/2.sce b/689/CH16/EX16.2/2.sce new file mode 100644 index 000000000..7a80b8792 --- /dev/null +++ b/689/CH16/EX16.2/2.sce @@ -0,0 +1,46 @@ +clc; funcprot(0);
+//Example 16.2 Horsepower required at sea level
+// Initialisation of variables
+W = 4225;
+b1 = 38;
+b2 = 35;
+Gap = 5.35;
+S1 = 214;
+S2 = 150;
+Dp = 9.4; // Parasite drag equivalent
+
+// Calculations
+mu =b2/b1;
+Gab_MeanSpan = 2*Gap/(b1+b2);
+S = S1 + S2;
+sigma = 0.56; //From fig 10.10
+r = S2/S1;
+K = mu*(1+r)/sqrt(mu^2 + 2*sigma*r*mu + r^2);
+EMAR = K^2*b1^2/S;
+Coeff_Cdi = 1/(%pi*EMAR);
+Cdp = 1.28*Dp/S;
+Coeff_Cl = W/(0.00256*S)
+Coeff_HPTot = 0.00256*S/375;
+
+V = [54 60 70 80 90 100 110 120 130 140 150];
+Cl = Coeff_Cl*diag(inv(diag(V^2)));
+Cd0 = [0.043 0.019 0.013 0.011 0.010 0.010 0.010 0.009 0.009 0.009 0.009]
+Cdi = Cl^2*Coeff_Cdi;
+Cd = Cd0+Cdi'+Cdp;
+Hp = Coeff_HPTot*diag(diag(V^3)*diag(Cd));
+Result = zeros(11,6);
+Result(:,1) = V';
+Result(:,2) = Cl;
+Result(:,3) = Cd0';
+Result(:,4) = Cdi;
+Result(:,5) = Cd';
+Result(:,6) = Hp;
+
+disp(Result,"!! V Cl Cd0 Cdi Cd HP Req !!") ;
+clf();
+plot2d(Result(:,1),Result(:,6));
+xlabel("Miles Per Hour");
+ylabel("HorsePower");
+title("Horsepower required for various airspeeds ");
+set(gca(),"grid",[1 1])
+
diff --git a/689/CH16/EX16.3/3.pdf b/689/CH16/EX16.3/3.pdf Binary files differnew file mode 100644 index 000000000..8bf04ba2c --- /dev/null +++ b/689/CH16/EX16.3/3.pdf diff --git a/689/CH16/EX16.3/3.sce b/689/CH16/EX16.3/3.sce new file mode 100644 index 000000000..a3bd7dbe2 --- /dev/null +++ b/689/CH16/EX16.3/3.sce @@ -0,0 +1,33 @@ +clc; funcprot(0);
+//Example 16.3 Horsepower required at sea level
+// Initialisation of variables
+W = 11200;
+S = 365;
+rho = 0.002378;
+
+// Calculations
+Cl = poly(0,'Cl');
+Cd = 0.023 + 0.0445*Cl^2;
+Coeff_Velo = 19.77*sqrt(W/S); //Using equtaion 8.5.2
+Coeff_HP = W^1.5/(550*sqrt(rho*S/2)); //Using equation 8.16.1
+Cl = [0.2 0.3 0.4 0.6 0.8 1.0 1.2 1.4]';
+
+
+Result = zeros(8,8);
+Result(:,1) = Cl;
+Result(:,2) = Cl^2;
+Result(:,3) = sqrt(Cl);
+Result(:,4) = Cl^1.5;
+Result(:,5) = horner(Cd,Cl);
+Result(:,6) = diag(diag(Result(:,5))*inv(diag(Result(:,4))));
+Result(:,7) = Coeff_HP*Result(:,6);
+Result(:,8) = Coeff_Velo*diag(inv(diag(Result(:,3))));
+
+disp(Result,"!!Cl Cl^2 Cl^0.5 Cl^1.5 Cd Cd/Cl^1.5 Hp req V(mph) !!") ;
+clf();
+plot2d(Result(:,8),Result(:,7));
+xlabel("Miles Per Hour");
+ylabel("HorsePower");
+title("Power Curves ");
+set(gca(),"grid",[1 1])
+
diff --git a/689/CH16/EX16.4/4.pdf b/689/CH16/EX16.4/4.pdf Binary files differnew file mode 100644 index 000000000..fa6429c0b --- /dev/null +++ b/689/CH16/EX16.4/4.pdf diff --git a/689/CH16/EX16.4/4.sce b/689/CH16/EX16.4/4.sce new file mode 100644 index 000000000..99ea92016 --- /dev/null +++ b/689/CH16/EX16.4/4.sce @@ -0,0 +1,26 @@ +clc; funcprot(0);
+//Example 16.4 Power required at level flight at altitude
+a10K = 1.16;
+a15K = 1.26;
+alp = [-4 -3 -2 -1 0 4 8 12 16 18 19]'; //From table 16.1
+V = [ 228 161 130 112 100 74.9 62.3 55.2 50.2 48.1 48.1]'; //From table 16.1
+HPreq = [566 199 111 76 60 34 29 29 30 31 33]'; //From table 16.1
+
+Result = zeros(11,7);
+Result(:,1) = alp;
+Result(:,2) = V;
+Result(:,3) = HPreq;
+Result(:,4) = a10K*V;
+Result(:,5) = a10K*HPreq;
+Result(:,6) = a15K*V;
+Result(:,7) = a15K*HPreq;
+
+disp(Result,"!!AlphaSL V_SL HPreq_SL V_10K HPreq_10K V_15K HPreq_15K !!") ;
+clf();
+plot2d([Result(:,2),Result(:,4),Result(:,6)],[Result(:,3),Result(:,5),Result(:,7)],rect = [0 ,0,180,180]);
+legend(['Sealevel';'10,000 altitude'; '15,000 altitude'],2);
+xlabel("Miles Per Hour");
+ylabel("HorsePower");
+title("Power Curves ");
+set(gca(),"grid",[1 1])
+
diff --git a/689/CH17/EX17.1/1.sce b/689/CH17/EX17.1/1.sce new file mode 100644 index 000000000..b3a0bd1c0 --- /dev/null +++ b/689/CH17/EX17.1/1.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 17.1 Absolute and service ceilings
+//Variable Initialisation
+W = 4000;
+DelHp0 = 60;
+DelHp10K = 17;
+
+//Calculation
+RC0 = DelHp0*33000/W;
+RC10K = DelHp10K*33000/W;
+H = 10000/(1 - (RC10K/RC0));
+Hs = H*(RC0-100)/RC0;
+
+//Results
+disp(Hs,"Service Ceiling (ft) : ");
diff --git a/689/CH17/EX17.2/2.sce b/689/CH17/EX17.2/2.sce new file mode 100644 index 000000000..ea0ebc51e --- /dev/null +++ b/689/CH17/EX17.2/2.sce @@ -0,0 +1,11 @@ +clc; funcprot(0);
+//Example 17.2 Time to Climb Altitude
+//Variable Initialisation
+RC0 = 1000; //Rate of climb at sea level
+H = 15000; //Absolute Ceiling
+h = 7000; // Height to climb
+
+//Calculation
+t = H*log(H/(H-h))/RC0;
+//Results
+disp(t,"Time to climb (min) : ");
diff --git a/689/CH17/EX17.3/3.sce b/689/CH17/EX17.3/3.sce new file mode 100644 index 000000000..40e274eec --- /dev/null +++ b/689/CH17/EX17.3/3.sce @@ -0,0 +1,11 @@ +clc; funcprot(0);
+//Example 17.2 Time to Climb Formula
+//Variable Initialisation
+h1 = 8000;
+h2 = 13600;
+
+//Calculation
+H = h1^2/(2*h1-h2);
+
+//Results
+disp(H,"Ceiling (ft) : ");
diff --git a/689/CH2/EX2.1/1.sce b/689/CH2/EX2.1/1.sce new file mode 100644 index 000000000..432479918 --- /dev/null +++ b/689/CH2/EX2.1/1.sce @@ -0,0 +1,17 @@ +//Example 2.1 On Law Of Continuity
+
+// Initialisation of variables
+dA_by_dS = -0.1;
+A = 4;
+V = 90;
+
+// Calculations
+dV_by_dS = -1*V*dA_by_dS/A;
+if(dV_by_dS > 0 ) then
+ flag = "Increasing";
+else flag = "Decreasing";
+end
+
+//Results
+disp(dV_by_dS,flag, "The Velocity (ft/sec)is :");
+
diff --git a/689/CH2/EX2.2/2.sce b/689/CH2/EX2.2/2.sce new file mode 100644 index 000000000..0da671cc4 --- /dev/null +++ b/689/CH2/EX2.2/2.sce @@ -0,0 +1,23 @@ +//Example 2.2 On Bernoulli's Equation
+
+// Initialisation of variables
+D1 = 8;
+P1 = 20*144; //Gage Pressure in lb per square feet
+q = 1000; //Rate of flow in gallon per minute.
+D2 = 4;
+Patm = 2116.2;
+rho = 62.4;
+
+// Calculations
+q = q*231/(1728*60); //Rate of flow in ft^3/sec
+A1 = %pi*(D1/12/2)^2; // Area in ft^2
+A2 = %pi*(D2/12/2)^2;
+V1 = q/A1;
+V2 = q/A2;
+P1_abs = P1 + Patm;
+P2_abs = P1_abs + (1/2)*rho*(V1^2 - V2^2)/32.2; // Bernoulli's Equation
+P2 = (P2_abs - Patm)/144;
+
+//Results
+disp(P2, "The gage pressure in pipe at D = 4 inch (lb per sq in) :");
+
diff --git a/689/CH2/EX2.3/3.sce b/689/CH2/EX2.3/3.sce new file mode 100644 index 000000000..cad8802a7 --- /dev/null +++ b/689/CH2/EX2.3/3.sce @@ -0,0 +1,17 @@ +//Example 2.3 On Venturi Tube
+
+// Initialisation of variables
+Da = 12 / 12;
+Db = 6 / 12;
+DP = 5*70.73; //Pressure difference in lb per sq feet
+rho = 62.4;
+
+// Calculations
+Ab = %pi*(Db/2)^2;
+Ab_Aa = (Db/Da)^2;
+Denominator = (rho/2)*(1 - Ab_Aa^2)/32.2;
+Q = Ab*sqrt(DP/Denominator); //Formula for venturi tube
+
+//Results
+disp(Q, "Flow rate (cu ft per sec) :");
+
diff --git a/689/CH2/EX2.4/4.sce b/689/CH2/EX2.4/4.sce new file mode 100644 index 000000000..6780f099b --- /dev/null +++ b/689/CH2/EX2.4/4.sce @@ -0,0 +1,14 @@ +//Example 2.4 On Stagnation Point
+
+// Initialisation of variables
+h = 50;
+v = 12*5280/3600; //Speed in feet/sec
+w = 62.4;
+
+// Calculations
+Po = w*h;
+Ps = Po + (1/2)*w*v^2/32.2;
+
+//Results
+disp(Ps/144, "Impact Pressure on nose (lb/sq-in):");
+
diff --git a/689/CH2/EX2.5/5.sce b/689/CH2/EX2.5/5.sce new file mode 100644 index 000000000..7cbd5cf84 --- /dev/null +++ b/689/CH2/EX2.5/5.sce @@ -0,0 +1,17 @@ +//Example 2.5 On Stagnation Point
+
+// Initialisation of variables
+h = 50;
+v = 100*5280/3600; //Speed in feet/sec
+rho_0 = 0.002378;
+rho_10000 = 0.001756;
+
+// Calculations
+Po = w*h;
+Ps_Po1 = (1/2)*rho_0*v^2;
+Ps_Po2 = (1/2)*rho_10000*v^2;
+V = 0.682*sqrt(Ps_Po2/(rho_0/2));
+
+//Results
+disp(V, "Part(c) Reading of airspeed indicator (mph):", Ps_Po2,"Part (b) difference between impact and static pressure at altitude 10000 ft(lb/sq-ft):", Ps_Po1,"Part (a) difference between impact and static pressure at sea level (lb/sq-ft):");
+
diff --git a/689/CH2/EX2.6/6.sce b/689/CH2/EX2.6/6.sce new file mode 100644 index 000000000..a8c19f359 --- /dev/null +++ b/689/CH2/EX2.6/6.sce @@ -0,0 +1,17 @@ +//Example 2.6 On Velocity and Stream Function
+
+// Initialisation of variables
+function[z] = shi(x,y)
+ z = x^2 - y^2;
+endfunction
+
+// Calculations
+h = 0.00001;
+u = (shi(3,2+h)-shi(3,2))/h; // Partial derivative wrt y
+v = -(shi(3+h,2)-shi(3,2))/h;
+Velo = sqrt(u^2+v^2);
+theta = atand(v/u);
+
+//Results
+disp(theta,"Anticlockwise angle at P(3,2) (Degree)", Velo, "Magnitude of velocity at P(3,2) (ft/sec)");
+
diff --git a/689/CH2/EX2.7/7.sce b/689/CH2/EX2.7/7.sce new file mode 100644 index 000000000..6f2bbe803 --- /dev/null +++ b/689/CH2/EX2.7/7.sce @@ -0,0 +1,21 @@ +//Example 2.7 Uniform Flow Plus a Source
+
+// Initialisation of variables
+U = 100;
+m = 600;
+P0 = 2116.2;
+rho = 0.002378;
+function[z] = shi(x,y)
+ z = -U*y + (m/(2*%pi)*atan(y/x));
+endfunction
+
+// Calculations
+h = 0.000001;
+u = (shi(h,1.5+h)-shi(h,1.5))/h ; // Partial derivative is ts taken in just the neighbourhood of 0 as if we take absolute zero then there will be a divide by zero error.
+v = -(shi(2*h,1.5)-shi(h,1.5))/h ;
+Velo = sqrt(u^2+v^2);
+P = P0 - (rho/2)*(Velo^2-U^2);
+
+//Results
+disp(P,"Pressure at P(0, 1.5) (lb/sq-ft)");
+
diff --git a/689/CH2/EX2.8/8.sce b/689/CH2/EX2.8/8.sce new file mode 100644 index 000000000..706c61575 --- /dev/null +++ b/689/CH2/EX2.8/8.sce @@ -0,0 +1,26 @@ +//Example 2.8 Source Plus Sink Plus Uniform Flow
+
+// Initialisation of variables
+
+U = -100;
+m = 314.2;
+P0 = 2116.2;
+rho = 0.002378;
+c = 1;
+x = 1.05;
+y = 0.6;
+P0 = 2116.2;
+function[z] = shi(x,y)
+ z = -U*y + (m/(2*%pi)*atan(2*c*y/(x^2-y^2-c^2)));
+endfunction
+
+// Calculations
+h = 0.00001;
+u = (shi(x,y+h)-shi(x,y))/h ;
+v = -(shi(x+h,y)-shi(x,y))/h ;
+Velo = sqrt(u^2+v^2);
+P = P0 - (rho/2)*(Velo^2-U^2);
+
+//Results
+disp(P,"Pressure at P(1.05, 0.6) (lb/sq-ft)");
+
diff --git a/689/CH2/EX2.9/9.sce b/689/CH2/EX2.9/9.sce new file mode 100644 index 000000000..2eaa7755d --- /dev/null +++ b/689/CH2/EX2.9/9.sce @@ -0,0 +1,14 @@ +//Example 2.9 Flow around a circular cylinder
+
+// Initialisation of variables
+P0 = 2116.2;
+U = 100;
+rho = 0.002378;
+theta = 15;
+
+// Calculations
+P = P0 + rho*U^2*(1 - 4*sind(theta)^2)/2;
+
+//Results
+disp(P,"Pressure at a point on the surface of cylinder (lb/sq-ft)");
+
diff --git a/689/CH3/EX3.1/1.sce b/689/CH3/EX3.1/1.sce new file mode 100644 index 000000000..331eb6908 --- /dev/null +++ b/689/CH3/EX3.1/1.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 3.1 Equation of states
+
+// Initialisation of variables
+T = 45+459.4;
+P = 25.93;
+P0 = 29.92;
+T0 = 518.4;
+rho_0 = 0.002378
+
+// Calculations
+rho = P*rho_0*T0/(P0*T);
+
+//Results
+disp(rho , "Density of dry air when pressure is 25.93 inch (pound/inch3):");
+
diff --git a/689/CH3/EX3.2/2.sce b/689/CH3/EX3.2/2.sce new file mode 100644 index 000000000..8ca4c518e --- /dev/null +++ b/689/CH3/EX3.2/2.sce @@ -0,0 +1,18 @@ +clc; funcprot(0);
+//Example 3.2 Equation of states
+
+// Initialisation of variables
+T = -10+459.4;
+P = 16.38;
+P0 = 29.92;
+T0 = 518.4;
+rho_0 = 0.002378
+g = 32.1740;
+
+// Calculations
+rho = P*rho_0*T0/(P0*T);
+W = rho*g;
+
+//Results
+disp(W , "Spwcific gravity of dry air (lb/ft3):");
+
diff --git a/689/CH3/EX3.3/3.sce b/689/CH3/EX3.3/3.sce new file mode 100644 index 000000000..593cdd39d --- /dev/null +++ b/689/CH3/EX3.3/3.sce @@ -0,0 +1,18 @@ +clc; funcprot(0);
+//Example 3.3 On Adiabatic Process
+
+// Initialisation of variables
+gma = 1.4;
+rho_0 = 0.002378;
+P1 = 2*2116.2; // Pressure ion lb per sq ft
+P0 = 1*2116.2; // Pressure ion lb per sq ft
+T0 = 59+459.4;
+
+// Calculations
+rho1 = rho_0*(P1/P0)^(1/gma);
+T1 =T0*(rho_0/rho1)*(P1/P0);
+
+//Results
+
+disp(T1-459.4 , "(b)Temperature if air is compressed adiabatically to 2 atm (degree farenheit):",rho1, "(a)Density if air is compressed adiabatically to 2 atm (Slug per cu ft):");
+
diff --git a/689/CH3/EX3.4/4.sce b/689/CH3/EX3.4/4.sce new file mode 100644 index 000000000..f110b6f19 --- /dev/null +++ b/689/CH3/EX3.4/4.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 3.4 On Speed of sound
+
+// Initialisation of variables
+gma = 1.4;
+g = 32.174;
+R = 53.351;
+T = 59+459.4;
+
+// Calculations
+a = sqrt(gma*g*R*T);
+//Results
+disp(a , "Speed of sound in standard temperature 59 degree farenheit (ft/sec):");
+
diff --git a/689/CH3/EX3.5/5.sce b/689/CH3/EX3.5/5.sce new file mode 100644 index 000000000..95c64eeb7 --- /dev/null +++ b/689/CH3/EX3.5/5.sce @@ -0,0 +1,13 @@ +clc; funcprot(0);
+//Example 3.5 Speed of sound
+
+// Initialisation of variables
+gma = 1.4;
+P = 2116.2;
+rho = 0.002378;
+
+// Calculations
+a = sqrt(gma*P/rho);
+//Results
+disp(a , "Speed of sound in standard pressure 2116.2 lbper sq ft, and standard density 0.002378slug per cu ft. (in ft/sec):");
+
diff --git a/689/CH3/EX3.6/6.sce b/689/CH3/EX3.6/6.sce new file mode 100644 index 000000000..477408485 --- /dev/null +++ b/689/CH3/EX3.6/6.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 3.6 Bernoulli Equation for compressible flow
+
+// Initialisation of variables
+gma = 1.4;
+P0 = 14.7;
+rho = 0.002378;
+V0= 500;
+P1 = 13.5;
+
+// Calculations
+a0 = sqrt(gma*P/rho);
+V1 =sqrt(V0^2 + 2*a0^2*(1-(P1/P0)^(1-1/gma))/(gma-1));
+
+//Results
+disp(V1 , "Speed of sound when pressure is 13.5 lb per sq in (in ft/sec):");
diff --git a/689/CH3/EX3.7/7.sce b/689/CH3/EX3.7/7.sce new file mode 100644 index 000000000..0f48b741c --- /dev/null +++ b/689/CH3/EX3.7/7.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 3.7 Similar Flows
+
+// Initialisation of variables
+c = 3/12; //chord length in feet
+V = 100*1.467; // velocity in ft/sec
+R = 0.002378;
+mu = 0.000000373;
+
+// Calculations
+RN = rho*V*c/mu;
+//Results
+disp(RN , "Reynolds no:");
+
diff --git a/689/CH4/EX4.1/1.sce b/689/CH4/EX4.1/1.sce new file mode 100644 index 000000000..daa2a3ecd --- /dev/null +++ b/689/CH4/EX4.1/1.sce @@ -0,0 +1,19 @@ +clc; funcprot(0);
+//Example 4.1 Standard Pressure at Altitude Below 35332 Feet
+
+// Initialisation of variables
+Z = 18000;
+a = 0.003566;
+P0 = 29.92;
+T0 = 518.4;
+R = 53.33;
+rho_0 = 0.002378;
+
+// Calculations
+T = T0 - a*Z;
+P = P0*(T/T0)^(1/a/R);
+rho = rho_0*P*T0/(P0*T);
+
+//Results
+disp(rho,"Density (slug per cu ft):",P,"Pressure (inch Hg):", T-459.4, "Temperature (Degree Farenheit):", "!---At an altitude of 18000 ft in standard altitude ---! ");
+
diff --git a/689/CH4/EX4.2/2.sce b/689/CH4/EX4.2/2.sce new file mode 100644 index 000000000..ef265620c --- /dev/null +++ b/689/CH4/EX4.2/2.sce @@ -0,0 +1,19 @@ +clc; funcprot(0);
+//Example 4.2 Standard Pressure at Altitude After 35332 Feet
+
+// Initialisation of variables
+P0 = 6.925;
+Z = 40000;
+R = 53.33;
+Z0 = 35332;
+T = 392.4;
+rho_0 = 0.002378;
+P0_SL = 29.92; // Pressure at sea level
+
+// Calculations
+P = P0*%e^((-Z+Z0)/(R*T));
+rho = rho_0 *P*T0/(P0_SL*T);
+
+//Results
+disp(rho,"Density (slug per cu ft):",P,"Pressure (inch Hg):", "!---At an altitude of 40000 ft in standard altitude ---! ");
+
diff --git a/689/CH4/EX4.3/3.sce b/689/CH4/EX4.3/3.sce new file mode 100644 index 000000000..31751d1b1 --- /dev/null +++ b/689/CH4/EX4.3/3.sce @@ -0,0 +1,18 @@ +clc; funcprot(0);
+//Example 4.3 Effect of Humidity
+
+// Initialisation of variables
+Dry_Bulb = 80;
+Wet_Bulb = 76;
+Factor = 1.68;
+P = 29.92;
+T = 459.4+80;
+P = 29.30;
+Var3_by_8e = 0.30; // From Graph
+
+// Calculations
+Dew_Point = Dry_Bulb - (Dry_Bulb-Wet_Bulb)*Factor;
+rho = 0.04120*(P - Var3_by_8e)/T;
+//Results
+disp(rho,"Density of the air when the temperature is 80 degree celcius(slug per cu ft):",Dew_Point,"Dew_Point :");
+
diff --git a/689/CH5/EX5.1/1.sce b/689/CH5/EX5.1/1.sce new file mode 100644 index 000000000..ae484aa13 --- /dev/null +++ b/689/CH5/EX5.1/1.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 5.1 Flat Plates Nornmal to Direction to Flow
+
+// Initialisation of variables
+l = 10;
+h = 8;
+V = 40;
+
+// Calculations
+A = l*h;
+F = 0.00327*A*V^2;
+
+//Results
+disp(F,"Force in plate (lb) :");
+
diff --git a/689/CH5/EX5.2/2.sce b/689/CH5/EX5.2/2.sce new file mode 100644 index 000000000..2d8ccaf0f --- /dev/null +++ b/689/CH5/EX5.2/2.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 5.2 Flat Plates Nornmal to Direction to Flow
+
+// Initialisation of variables
+V1 = 1;
+F1 = 0.012;
+V2 = 35;
+
+// Calculations
+A = F1/(0.00327*V1^2)
+F2 = 0.00327*A*V2^2;
+
+//Results
+disp(F2,"Force on windshield when wind velocity is 35 mph (lb) :");
+
diff --git a/689/CH5/EX5.3/3.sce b/689/CH5/EX5.3/3.sce new file mode 100644 index 000000000..b32d1f1fc --- /dev/null +++ b/689/CH5/EX5.3/3.sce @@ -0,0 +1,19 @@ +clc; funcprot(0);
+//Example 5.3 Curved Deflecting Surface
+
+// Initialisation of variables
+eps = 4;
+rho = 0.002378;
+w = 50;
+h = 10;
+V = 88; // Velocity in ft per seconds
+
+// Calculations
+A = w*h;
+F = rho*A*V^2*sqrt(2*(1-cosd(eps)));
+Fh = rho*A*V^2*(1-cosd(eps));
+Fv = rho*A*V^2*sind(eps);
+
+//Results
+disp(Fv,"Vertical component of Force(lb) :",Fh,"Horizontal component of Force(lb:)", F,"Net Force(lb) :", "!----Magnitude of force required deflect 4 degree ddownward without loss in speed ----!");
+
diff --git a/689/CH5/EX5.4/4.sce b/689/CH5/EX5.4/4.sce new file mode 100644 index 000000000..a17dceaa7 --- /dev/null +++ b/689/CH5/EX5.4/4.sce @@ -0,0 +1,21 @@ +clc; funcprot(0);
+//Example 5.4 Inclined Flat Plates
+
+// Initialisation of variables
+Cl = 0.73; // From Figure
+Cd = 0.164; // From Figure
+l = 12;
+w = 2;
+alpha = 12;
+V = 50;
+rho = 0.002378;
+
+// Calculations
+A = l*w;
+L = (Cl*rho*A*V^2)/2;
+D = (Cd*rho*A*V^2)/2;
+R = sqrt(L^2+D^2);
+
+//Results
+disp(R,"Total Force (lb) :", D ,"Force Parallel to Airstream (lb):",L,"Force Parallel to Airstream (lb):");
+
diff --git a/689/CH7/EX7.1/1.sce b/689/CH7/EX7.1/1.sce new file mode 100644 index 000000000..c175ba051 --- /dev/null +++ b/689/CH7/EX7.1/1.sce @@ -0,0 +1,23 @@ +clc; funcprot(0);
+//Example 7.1 Pressure distribution in real fluid
+
+// Initialisation of variables
+ky_U = [-1.56 -4.00 -1.58 -2.71 -3.01 -7.36 -2.88 -4.40 -1.58 -2.20 -0.64 -0.60 -0.04];
+ky_L = [-0.91 0.93 0.49 0.89 1.22 2.52 1.10 1.92 .86 1.56 0.70 1.16 0.23];
+x = 0.1;
+alpha = 16;
+
+i = 1;L = 0; U = 0;
+while(i < = length(ky_L)),
+ L = L + ky_L(i);
+ U = U + ky_U(i);
+ i = i + 1 ;
+end
+
+// Calculations
+Cn = x*(abs(L) + abs(U))/3;
+Cc = -0.34;
+Cl = Cn*cosd(alpha)-Cc*sind(alpha);
+
+//Results
+disp(Cl,"Lift Coefficient :");
\ No newline at end of file diff --git a/689/CH8/EX8.1/1.sce b/689/CH8/EX8.1/1.sce new file mode 100644 index 000000000..db929df26 --- /dev/null +++ b/689/CH8/EX8.1/1.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 8.1 Lift Equation
+
+// Initialisation of variables
+V = 100*1.467; // Velocity in ft/s
+alpha =4;
+S = 250; //Wing Area.
+rho = 0.00237;
+
+// Calculations
+Cl = 0.649; // From figure 8.8
+W = Cl*rho/2*S*V^2;
+
+//Results
+disp(W,"Weight with which an airplane can fly with Clark Y wing (lb) :");
\ No newline at end of file diff --git a/689/CH8/EX8.10/10.sce b/689/CH8/EX8.10/10.sce new file mode 100644 index 000000000..2f358741d --- /dev/null +++ b/689/CH8/EX8.10/10.sce @@ -0,0 +1,19 @@ +clc; funcprot(0);
+//Example 8.10 Polar Curves
+
+// Initialisation of variables
+W = 2000;
+S = 180;
+V = 120*1.467;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*(W/S)/(rho*V^2);
+Cd = 0.019 ; //From fig 8.19
+LbyD = Cl/Cd;
+L = W; // for level flight lift = weight
+D = L/LbyD;
+HP = D*V/550;
+
+//Results
+disp(HP,"Horse power required to move the wing forward(hp) :");
\ No newline at end of file diff --git a/689/CH8/EX8.11/11.sce b/689/CH8/EX8.11/11.sce new file mode 100644 index 000000000..772b0ce81 --- /dev/null +++ b/689/CH8/EX8.11/11.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.11 Absolute Coefficients with metric units
+
+// Initialisation of variables
+S = 35;
+V = 40;
+alpha = 4;
+rho = 0.125;
+
+// Calculations
+Cl = 0.76; // Value of Cl from fig 8.10
+L = Cl*(rho/2)*S*V^2;
+//Results
+disp(L,"Required Lift (Kg):");
\ No newline at end of file diff --git a/689/CH8/EX8.12/12.sce b/689/CH8/EX8.12/12.sce new file mode 100644 index 000000000..1c4aad08e --- /dev/null +++ b/689/CH8/EX8.12/12.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.12 Absolute Coefficients with metric units
+
+// Initialisation of variables
+WbyS = 30; //Wing loading(kg/m^2)
+V = 40;
+alpha = 2;
+rho = 0.125;
+
+// Calculations
+Cl = 0.585; // Value of Cl from fig 8.10
+V = sqrt(2*WbyS/(rho*Cl));
+//Results
+disp(V,"Required speed (m/s):");
\ No newline at end of file diff --git a/689/CH8/EX8.13/13.sce b/689/CH8/EX8.13/13.sce new file mode 100644 index 000000000..09cbe797b --- /dev/null +++ b/689/CH8/EX8.13/13.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.13 Power in terms of Cd/Cl^3/2
+
+// Initialisation of variables
+W = 4000;
+S = 300;
+Cl = 1.2;
+Cd = 0.1;
+rho = 0.002378;
+// Calculations
+HP = (W/550)*(Cd/Cl^1.5)*sqrt(W/S)/sqrt(rho/2);
+
+//Results
+disp(HP,"Required Horse Power(hp):");
\ No newline at end of file diff --git a/689/CH8/EX8.14/14.sce b/689/CH8/EX8.14/14.sce new file mode 100644 index 000000000..c2f85347f --- /dev/null +++ b/689/CH8/EX8.14/14.sce @@ -0,0 +1,20 @@ +clc; funcprot(0);
+//Example 8.14 Moment Coefficient and center of pressure
+
+// Initialisation of variables
+alpha = 2;
+V = 120;
+b = 42;
+c = 7;
+rho = 0.002378;
+
+// Calculations
+S = b*c;
+Cl = 0.295; //From fig 8.13
+Cd = 0.0156; //From fig 8.13
+CP = .36; //From fig 8.13
+CMo = -CP*(Cl*cosd(alpha)+Cd*sind(alpha));
+Mo = CMo*C*S*V^2*(rho/2);
+
+//Results
+disp(Mo,"Moment about leading edge (ft-lb):");
diff --git a/689/CH8/EX8.15/15.sce b/689/CH8/EX8.15/15.sce new file mode 100644 index 000000000..49dab16ab --- /dev/null +++ b/689/CH8/EX8.15/15.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 8.15 Center of Pressure
+
+// Initialisation of variables
+WbyS = 8; //Wing Loading
+V = 100*1.467;
+CMo = -0.067;
+
+// Calculations
+Cl = (2*WbyS/(rho*V^2))
+CM_qtrChrd = CMo;
+CP = 0.25 - CM_qtrChrd/Cl;
+
+//Results
+disp(CP*100,"Center of Pressure in % of chord length:");
\ No newline at end of file diff --git a/689/CH8/EX8.16/16.sce b/689/CH8/EX8.16/16.sce new file mode 100644 index 000000000..74fa68127 --- /dev/null +++ b/689/CH8/EX8.16/16.sce @@ -0,0 +1,15 @@ +clc; funcprot(0);
+//Example 8.16 Center of Pressure
+
+// Initialisation of variables
+CMo = -0.27;
+alpha = 6;
+Cl = 0.84;
+Cd = 0.06;
+
+// Calculations
+CP_approx = -CMo/Cl;
+CP_exact = -CMo/(Cl*cosd(alpha)+Cd*sind(alpha));
+
+//Results
+disp(CP_exact*100,"Exact CP (%chord length) :",CP_approx*100,"Approximate CP (%chord length)");
\ No newline at end of file diff --git a/689/CH8/EX8.2/2.sce b/689/CH8/EX8.2/2.sce new file mode 100644 index 000000000..ef80c4492 --- /dev/null +++ b/689/CH8/EX8.2/2.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.2 Lift Equation
+
+// Initialisation of variables
+V = 90*1.467; // Velocity in ft/s
+S = 300; //Wing Area.
+rho = 0.00237;
+W = 3000;
+
+// Calculations
+Cl = W*2/(rho*S*V^2); // From figure 8.8
+
+//Results
+disp("Corrosponding value of alpha for the above Lift Coefficient is 1.7 degree (from fig 8.8).",Cl,"Lift Coefficient for the above data is :");
diff --git a/689/CH8/EX8.3/3.sce b/689/CH8/EX8.3/3.sce new file mode 100644 index 000000000..aadfeb0f0 --- /dev/null +++ b/689/CH8/EX8.3/3.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.3 Lift Equation
+
+// Initialisation of variables
+W_by_S = 9;
+rho = 0.002378;
+alpha = 6 ;
+Cl = 0.791; // Value of Cl from fig 8.8
+
+// Calculations
+V = sqrt(W_by_S*2/(rho*Cl));
+
+//Results
+disp(V,"Velocity in ft/sec :");
\ No newline at end of file diff --git a/689/CH8/EX8.4/4.sce b/689/CH8/EX8.4/4.sce new file mode 100644 index 000000000..fd1f4d42a --- /dev/null +++ b/689/CH8/EX8.4/4.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 8.4 Power Required by Wing
+
+// Initialisation of variables
+S = 350;
+V = 80;
+alpha = 6;
+Cd = 0.0452; // Value of Cd from fig 8.8
+rho = 0.002378;
+
+// Calculations
+D = Cd*rho/2*S*V^2;
+HP = D*V/550;
+
+//Results
+disp(HP,"Horse power required to move the wing forward(hp) :",D,"Drag (lb):");
\ No newline at end of file diff --git a/689/CH8/EX8.5/5.sce b/689/CH8/EX8.5/5.sce new file mode 100644 index 000000000..284e76c7d --- /dev/null +++ b/689/CH8/EX8.5/5.sce @@ -0,0 +1,26 @@ +clc; funcprot(0);
+//Example 8.5 Flying Level at Altitude
+
+// Initialisation of variables
+W = 2000;
+S = 350;
+V = 100*1.467;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*(W/S)/(rho*V^2);
+alpha = -1.75; // From fig 8.15
+Cd = 0.014; // From fig 8.15
+D = Cd*(rho/2)*S*V^2;
+HP = D*V/550;
+
+// At 10000 ft altitude density is lower as compared to the density at sea level.
+rhoX = 0.001756;
+Cl = 2*(W/S)/(rhoX*V^2);
+alpha = -0.75; // From fig 8.15
+Cd = 0.016; // From fig 8.15
+D1 = Cd*(rhoX/2)*S*V^2;
+HP1 = D1*V/550;
+
+//Results
+disp(HP1,"Horse power required to move the wing forward(hp) :",D1,"Drag (lb):","!------Part (b)------!",HP,"Horse power required to move the wing forward(hp) :",D,"Drag (lb):","!------Part (a)------!");
\ No newline at end of file diff --git a/689/CH8/EX8.6/6.sce b/689/CH8/EX8.6/6.sce new file mode 100644 index 000000000..0a5bd7261 --- /dev/null +++ b/689/CH8/EX8.6/6.sce @@ -0,0 +1,26 @@ +clc; funcprot(0);
+//Example 8.5 Flying Level at Altitude
+
+// Initialisation of variables
+W = 4000;
+S = 350;
+V = 100*1.467;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*(W/S)/(rho*V^2);
+alpha = 1.5; // From fig 8.15
+Cd = 0.0217; // From fig 8.15
+D = Cd*(rho/2)*S*V^2;
+HP = D*V/550;
+
+// At 10000 ft altitude density is lower as compared to the density at sea level.
+rhoX = 0.001756;
+Cl = 2*(W/S)/(rhoX*V^2);
+alpha = 3.5; // From fig 8.15
+Cd = 0.0308; // From fig 8.15
+D1 = Cd*(rhoX/2)*S*V^2;
+HP1 = D1*V/550;
+
+//Results
+disp(HP1,"Horse power required to move the wing forward(hp) :",D1,"Drag (lb):","!------Part (b)------!",HP,"Horse power required to move the wing forward(hp) :",D,"Drag (lb):","!------Part (a)------!");
\ No newline at end of file diff --git a/689/CH8/EX8.7/7.sce b/689/CH8/EX8.7/7.sce new file mode 100644 index 000000000..2f303cadd --- /dev/null +++ b/689/CH8/EX8.7/7.sce @@ -0,0 +1,12 @@ +clc; funcprot(0);
+//Example 8.7 Lift Drag Ratio
+
+// Initialisation of variables
+W = 5000;
+LD_Max = 21.5;
+
+// Calculations
+D = W/LD_Max;
+
+//Results
+disp(D,"Minimum drag on clark Y wing (lb)");
\ No newline at end of file diff --git a/689/CH8/EX8.8/8.sce b/689/CH8/EX8.8/8.sce new file mode 100644 index 000000000..17f632111 --- /dev/null +++ b/689/CH8/EX8.8/8.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 8.8 Polar Curves
+
+// Initialisation of variables
+W = 3000;
+S = 350;
+V = 90;
+rho = 0.002378;
+
+// Calculations
+Cl = 2*W/(S*V^2);
+Cd = 0.0561; //From figure 8.18
+HP = Cd*rho*S*V^3/(2*550);
+
+//Results
+disp(HP,"Horse power required by wing (hp) : ");
\ No newline at end of file diff --git a/689/CH8/EX8.9/9.sce b/689/CH8/EX8.9/9.sce new file mode 100644 index 000000000..6e1681a69 --- /dev/null +++ b/689/CH8/EX8.9/9.sce @@ -0,0 +1,14 @@ +clc; funcprot(0);
+//Example 8.9 Polar Curve
+
+// Initialisation of variables
+Cl_clark = 0.43; //Values from fig 8.18
+Cd_clark = 0.020; //Values from fig 8.18
+Cl_USA = 0.55; //Values from fig 8.19
+Cd_USA = 0.03; //Values from fig 8.19
+// Calculations
+LbyD_clark = Cl_clark/Cd_clark;
+LbyD_USA = Cl_USA/Cd_USA;
+
+//Results
+disp(LbyD_clark,"Maximum L/D for clark Y :",LbyD_USA,"Maximum L/D for USA-35 :");
diff --git a/689/CH9/EX8.3/3.sce b/689/CH9/EX8.3/3.sce new file mode 100644 index 000000000..a67630ce9 --- /dev/null +++ b/689/CH9/EX8.3/3.sce @@ -0,0 +1,32 @@ +clc; funcprot(0);
+//Example 9.3 Horseshoe Vortex
+
+// Initialisation of variables
+T = 250;
+
+// Calculations
+function[y] =Velocity(R, theta1, theta2)
+ y = (T/(4*%pi*R))*(cos(theta1)-cos(theta2))
+endfunction
+//Considering Leg AB
+ theta1 = 0; //From figure
+ theta2 = %pi - atan(4/5); //From figure
+ R = 4; //From figure
+ Vt1 = Velocity(R, theta1, theta2);
+
+//Considering Leg BC
+ theta1 = atan(5/4); //From figure
+ theta2 = %pi - atan(5/6); //From figure
+ R = 5; //From figure
+ Vt2 = Velocity(R, theta1, theta2);
+
+//Considering Leg CD
+ theta1 = atan(5/6); //From figure
+ theta2 = %pi; //From figure
+ R = 6; //From figure
+ Vt3 = Velocity(R, theta1, theta2);
+
+Vt = Vt1 + Vt2 + Vt3;
+
+//Results
+disp(Vt,"Velocity at point P (ft/sec):",Vt3,"Velocity due to leg CD (ft/sec):",Vt2,"Velocity due to leg BC (ft/sec):",Vt1,"Velocity due to leg AB (ft/sec):");
diff --git a/689/CH9/EX9.1/1.sce b/689/CH9/EX9.1/1.sce new file mode 100644 index 000000000..3f764a5de --- /dev/null +++ b/689/CH9/EX9.1/1.sce @@ -0,0 +1,19 @@ +clc; funcprot(0);
+//Example 9.1 Lift due to Circulation
+
+// Initialisation of variables
+D = 4;
+L = 12;
+V = 40*1.467;
+rho = 0.002378;
+W = 100/60; // Revolution per second
+
+// Calculations
+R =D/2;
+Vt = 2*%pi*R*W;
+T = 2*%pi*R*Vt;
+Lift = rho*T*V;
+L_total = Lift*L
+
+//Results
+disp(L_total,"Total lifting force (lb):");
diff --git a/689/CH9/EX9.2/2.sce b/689/CH9/EX9.2/2.sce new file mode 100644 index 000000000..2aea7f8a2 --- /dev/null +++ b/689/CH9/EX9.2/2.sce @@ -0,0 +1,16 @@ +clc; funcprot(0);
+//Example 9.2 Biot Savart's Law
+
+// Initialisation of variables
+T = 500;
+PB = 2;
+BA1 = 3;
+
+// Calculations
+theta1 = atan(PB/BA1);
+theta2 = %pi/2;
+R = PB;
+Vt = (T/(4*%pi*R))*(cos(theta1)-cos(theta2));
+
+//Results
+disp(Vt,"Velocity at point P (ft/sec):");
\ No newline at end of file |