8 files changed, 144 insertions, 0 deletions
diff --git a/689/CH16/EX16.1/1.pdf b/689/CH16/EX16.1/1.pdf
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index 000000000..25d86c55f
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+++ b/689/CH16/EX16.1/1.pdf
diff --git a/689/CH16/EX16.1/1.sce b/689/CH16/EX16.1/1.sce
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+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
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index 000000000..fce023575
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+++ 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
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+++ 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
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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
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+++ 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
new 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])
+