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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: ( ) ϑ ϑ α ϑ γ sin cos 1 2 + = ∞ V which can be non-dimensionalized, ( ) ϑ ϑ α ϑ γ 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 ϑ ) position on the chord line. That is, ∞ − V V V lower upper α . 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 ϑ ) position on the chord line? Explain. From equation 4.8 in the text and Monday’s lecture, we know that lower upper V V − = γ The angular variable ϑ is related to chordwise position ξ by: c ξ ϑ 2 1 cos − = And so the velocity difference of interest can be solved as: ( ) ⎟ ⎟ ⎠ ⎞ ⎜ ⎜ ⎝...
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- Fall '09
- Airfoil, Vlower, Vupper