This preview shows pages 1–2. Sign up to view the full content.
This preview has intentionally blurred sections. Sign up to view the full version.View Full Document
Unformatted text preview: AAE 334, Fall 2011, Homework 5 Due Friday, September 2 at the beginning of class. We find in section 4.7 that the distribution of vortex strength on the chord of the symmetric airfoil is: ( ) sin cos 1 2 + = V which can be non-dimensionalized, ( ) sin cos 1 2 + = V . 1. Solve for and plot the non-dimensional difference between upper surface and lower surface velocities as a function of linear (not ) position on the chord line. That is, V V V lower upper . 2. Can you use results of part 1 to plot the difference between upper surface to lower surface pressure coefficients, ( ) lower p upper p c c , , as a function of linear (not ) position on the chord line? Explain. From equation 4.8 in the text and Mondays lecture, we know that lower upper V V = The angular variable is related to chordwise position by: c 2 1 cos = And so the velocity difference of interest can be solved as: ( )...
View Full Document
- Fall '09