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Unformatted text preview: Assume that the lift coefficient is a linear function of the angle of attack and that o 2 . 1= l α . If the load distribution is elliptic, calculate the following: a) Value of the circulation in the plane of symmetry, Γ . b) Downwash velocity, w . c) Induced drag coefficient, i D C . d) Geometric angle of attack, . e) Effective angle of attack, eff . 3. A certain wing has a total span of 10 m, root chord of 3 m, and a taper ratio of 0.6. The wing is composed of cambered airfoils with α L = 2 o at each section. The wing is linearly twisted geometrically such that the effective angle of attack changes linearly from 10 o at the root and 4 o at the tip. The aircraft is flying at 60 m/sec at sea level. Find a) the aspect ratio b) the wing area, and c) the lift per unit span at the wing semispan....
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 Summer '07
 Ruffin
 Aerodynamics, Lift, Airfoil, LOWSPEED AERODYNAMICS Assignment, law velocity function

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