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Q1solution - attack is approximately 6.28 The πα 2 = l c...

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AAE 334 Fall 2011 Quiz 1. SOLUTIONS Circle True or False or neither of the two. Points: +1 for correct, -1 for incorrect, 0 for blank. Ambiguous answers are scored as incorrect answers. All questions concern the classical thin airfoil theory which we have studied to date in the class. 1 True False The Kutta-Joukowsky theorem shows that lift is proportional to the product of vorticity (which we also call “circulation”) and dynamic pressure. velocity, not dynamic pressure 2 True False The chord line and the camber line differ except for symmetric airfoils. 3 True False The zero-lift angle of attack depends on airfoil shape and flight velocity. Is independent of flight velocity. 4 True False The definitions of the , , and coefficient include an integral of the slope of the thickness distribution of the airfoil. 0 A 1 A 2 A Slope of camber line, not of the thickness distribution. 5 True False The lift coefficient for a symmetric airfoil at 1 degree angle of
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Unformatted text preview: attack is approximately 6.28. The πα 2 = l c formula is for radians, not degrees. 6 True False The Kutta condition sets the induced velocity to be the negative of the normal component of the flight velocity everywhere on the camber line That’s a boundary condition, not the Kutta condition. 7 True False The Superlinear Principle of Position states that when we add together two velocity potentials, the sum is also a velocity potential. “Principle of Linear Superposition” says this. 8 True False The angle of attack is the angle between the chord line and the velocity vector of the free stream. 9 True False Bernoulli’s equation or law defines dynamic pressure, q, as 2 2 1 V q ρ = Uses dynamic pressure, doesn’t define it. 10 True False Thin airfoil theory is useful for airfoils with some but not too much thickness....
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