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+clear
+clc
+//Example 11.7 WING AREA FOR AN AIRPLANE
+T=-67+460; //temperature [°R]
+R=1716; //[ft.lbf/slug.°R]
+//1ft^2=144in^2
+p=3.3*144; //pressure[lbf/ft^2]
+rho=p/(R*T) //[slug/ft^3]
+CL=0.2;
+Vo=600; //[ft/s]
+W=10000; //weight [lbf]
+//for steady flight,
+FL=W 
+//Wing area
+S=2*W/(rho*Vo^2*CL) //[ft^2]
+b=54; //span of wing [ft]
+CDi=CL^2/(%pi*(b^2/S)) //min.induced drag coefficient
+//Induced drag
+Di=(rho*Vo^2*CDi*S)/2 //[lbf]
+printf("\nThe wing area = %.f ft^2 and the minimum induced drag = %.1f lbf.\n",S,Di)
+\ No newline at end of file