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# HW5 - position on the chord line That is ∞ − V V V...

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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
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Unformatted text preview: ) 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....
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