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+//Aeroplane
+//refer fig. 19.10
+r=1300 //m
+W=8 //kN
+v=(400*1000)/(60*60) //m/sec
+//Angle of bank
+alpha=atand((111.111^2)/(9.81*1300)) //degree
+//Lift under flight condition is
+N=80*((cosd(alpha))+(((sind(alpha))*111.111^2)/(9.81*1300))) //kN
+printf("\nalpha=%.2f degree\nN=%.2f kN",alpha,N)
+