Problem 3 Consider the supersonic flow over a 5 deg half-angle wedge at 15 angle of angle of attack. The freestream parameters are M=2 consider the density 1.23K(g)/(m^(')).P=1.31*10^(')Pa. The shear stress can be assumed to be zero in the contribution for lift and drag. The chord of the wedge is 2 m . Calculate the lift and drag coefficient. Hint

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Problem 3 Consider the supersonic flow over a

5\deg

half-angle wedge at 15 angle of angle of attack. The freestream parameters are

M=2

consider the density

1.23K(g)/(m^(')).P=1.31*10^(')Pa

. The shear stress can be assumed to be zero in the contribution for lift and drag. The chord of the wedge is 2 m . Calculate the lift and drag coefficient. Hint: determine the upper and lower pressure by the compressible flow theory Problem 4 Consider an NACA2412 airfoil with a 2 m chord in an airstream with a velocity of

70(m)/(s)

at standard sea level conditions. If the lift per unit span is 3500 N . What is the angle of attack in the degree?

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