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2004C Test 2

# 2004C Test 2 - AERO 201 Test 2 Fall 2004 Name(all problems...

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1. Consider a wing at an arbitrary angle of attack, α . The lift, L, and drag, D, forces are perpendicular and parallel to the freestream velocity, respectively. Develop the equations for the corresponding Normal (N) and Axial (A) forces as a function of L, D and α . 2. An aircraft is flying at standard sea level conditions. Given a a m m V 240 ; M 0.73; V 275 (assume M 1.0) s s = = = < , find the pressure, p a , at point ‘a’ on the wing. 3. Given the following equation 2 2 1 2 p 1 p 2 V V c T c T 2 2 + = + ° and given the following statements, indicate True (T) or False (F): a) flow is inviscid T F b) flow is incompressible T F c) flow is reversible T F d) flow is steady T F e) flow is adiabatic T F AERO 201 Test 2 Fall 2004 Name ____________________________________ (all problems are valued at 10% unless otherwise noted) a freestream “ ° o freestream “ ° α

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4. Given the pressure, p(x), on the wing as shown, where x is measured from the mid-chord, (note: for interpretation by simple observation, the distribution is a simple geometry and provides
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2004C Test 2 - AERO 201 Test 2 Fall 2004 Name(all problems...

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