Unformatted text preview: +15deg. Is the result a straight line or nearly so? Compare to the “thin airfoil” theory, which says Cl=2 π ( ∝-∝ _zl), where ∝ _zl is the angle of attack at which the lift is zero. You may take that number from the XFLR5 results (though later on you will learn how to calculate it from the camber). 3) Construct the lift/drag polar for the above airfoil. What is the max L/D for the airfoil, and what angle of attack gives it?...
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- Fall '09
- Aerodynamics, Lift, Airfoil, Angle of attack, skin friction, camber