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....
View Full Document
- Fall '09
- Airfoil, camber line, flight velocity