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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)
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