Unformatted text preview: wing, with a span efficiency factor of 0.85, is operating at a C L of 0.6. Assume = . a) What is the speed of the airplane? b) What is the induced drag on the airplane? c) The wing has a symmetric airfoil section with a 2-D lift curve slope of 0.105/degree. What is the geometric angle of attack of the wing? 3. Problem 5.4 from the text. 4. Problem 5.5 from the text....
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- Spring '07
- Aerodynamics, Lift, Airfoil, span efficiency factor, root chord length, tip chord length