H=2000;//standard altitude at which airplane is flying(meter)
P=7.95*10^4;//pressure corresponding to standard altitude,N/m^2
D=1.0066;//density corresponding to standard altitude,Kg/m^3
P1=7.58*10^4;//pressure at a point on wing,N/m^2
V=70;//airplane velocity in m/s
q=D*V^2/2 //dynamic pressure,N/m^2