diff options
Diffstat (limited to '689/CH10')
| -rw-r--r-- | 689/CH10/EX10.1/1.sce | 15 | ||||
| -rw-r--r-- | 689/CH10/EX10.10/10.sce | 33 | ||||
| -rw-r--r-- | 689/CH10/EX10.2/2.sce | 15 | ||||
| -rw-r--r-- | 689/CH10/EX10.3/3.sce | 16 | ||||
| -rw-r--r-- | 689/CH10/EX10.4/4.sce | 18 | ||||
| -rw-r--r-- | 689/CH10/EX10.5/5.sce | 13 | ||||
| -rw-r--r-- | 689/CH10/EX10.6/6.sce | 26 | ||||
| -rw-r--r-- | 689/CH10/EX10.7/7.sce | 22 | ||||
| -rw-r--r-- | 689/CH10/EX10.8/8.sce | 22 | ||||
| -rw-r--r-- | 689/CH10/EX10.9/9.sce | 20 | ||||
| -rw-r--r-- | 689/CH10/EX11.2/2.sce | 21 |
11 files changed, 221 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: ") ;
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