This preview has intentionally blurred sections. Sign up to view the full version.View Full Document
Unformatted text preview: AAE 334, Fall 2011, Homework 6 SOLUTION (sign error in #1 and #2 and plot in #3 corrected) Due Wednesday, September 7 at the beginning of class. In section 4.8 Anderson develops equation to determine chordwise position of the center of pressure, . Similarly, he solves for the pitching moment coefficients about the leading edge, , and about the quarter-chord point, . cp x le m c , 4 / , c m c 1. Show that , , and are independent of the coefficient for thin cambered airfoils if lift coefficient is constant (as may be a choice when designing an airfoil for steady level cruise.) cp x le m c , 4 / , c m c 1 A 2. Solve analytically for rate at which the chordwise location of the center of pressure varies with changes in angle of attack for thin cambered airfoils. (This problem is independent of problem 1.) 3. Plot versus angle of attack, , for the NACA 23012 airfoil in Example 4.6 in the text....
View Full Document
This note was uploaded on 02/21/2012 for the course AAE 334 taught by Professor Collicott during the Fall '09 term at Purdue.
- Fall '09