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V=100;//velocity of airplane(m/s)
H=3000;//standard altitude at which airplane is flying(meter)
Cp=-2.2;//pressure coefficient at a point on fuselage
P=7.0121*10^4;//pressure at 3000 m,N/m^2
D=0.90926;//density at 3000 m,Kg/m^3
q=D*V^2/2 //dynamic pressure,N/m^2
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