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+clc;
+clear all;
+disp("Heat loss from wing")
+U=450*1000/3600//m/s
+L=6;//m
+B=1.2;//m
+p=1.013*65/76*10^5;//Pa
+R=287;
+k=0.2511;//W/m.C
+v=14.16*10^(-6);//m^2/s
+Pr=0.705;
+ta=10;//degree C
+rho=p/(R*(ta+273));//kg/m^3
+ReL=U*B/v;
+Rec=5*10^5;
+xc=Rec*v/U;//m
+Nu=(0.036*ReL^0.8-836)*Pr^(1/3);
+h=Nu*k/B;
+A=L*B;
+delT=19-1;//degree C
+Q=h*A*delT;//W
+disp("W",Q,"Heat loss from wing =")
+Cf=(0.072/ReL^0.2-1670/ReL);
+Fd=Cf*0.5*rho*A*U^2;
+disp("N",Fd,"Drag force on the wing =")
+