EAS4101_S09_Test2 - EAS 4101 Aerodynamics Spring 2009...

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EAS 4101 Aerodynamics – Spring 2009 04/08/09, Exam #2 Name: ____________________________ 1 I. True/False (10 points total – 1 point each) Clearly circle T for true statements and F for false statements. 1. The lift force is always perpendicular to the chord line. T F 2. Kelvin’s Theorem relates lift and circulation. T F 3. Wing tip vortices are driven by the pressure difference between the upper and lower surfaces of a wing. T F 4. The effective angle of attack on a wing is always less than the geometric angle of attack. T F 5. The lift slope of a finite wing is always less than the lift slope of the corresponding airfoil. T F 6. The induced drag is not a function of wing geometry T F 7. The zero lift angle of attack for a symmetric airfoil is always zero. T F 8. Induced drag coefficient is proportional to g G ± . T F 9. The vorticity field is always solenoidal (i.e. divergence-free). T F 10. For a general lift distribution on a finite wing, the downwash is constant over the entire span. T F II. Fill in the Blank (17 points total – 1 point each) 11. The ____________________ is the distance from the leading edge of an airfoil to the point where there is zero aerodynamic moment. The ____________________ is the distance from the leading edge of an airfoil to a point about which the aerodynamic moment does not change with angle of attack. For a ____________________ airfoil of chord c , these points lie on top of each other and are at a distance ____________________ from the leading edge. 12. The Kutta condition is naturally enforced at the trailing edge due to ____________________ forces. 13. The point on an airfoil about which the aerodynamic moment is zero is called the ____________________. 14. Stokes’ Theorem is used show that ____________________ is ____________________ per unit area. 15.
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This note was uploaded on 09/05/2011 for the course EAS 4101 taught by Professor Sheplak during the Spring '08 term at University of Florida.

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EAS4101_S09_Test2 - EAS 4101 Aerodynamics Spring 2009...

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