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Unformatted text preview: attack is approximately 6.28. The 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 Thats 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 Bernoullis equation or law defines dynamic pressure, q, as 2 2 1 V q = Uses dynamic pressure, doesnt define it. 10 True False Thin airfoil theory is useful for airfoils with some but not too much thickness....
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This note was uploaded on 02/21/2012 for the course AAE 334 taught by Professor Collicott during the Fall '09 term at Purdue University-West Lafayette.
- Fall '09