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HW3 - 2 2 1 ∞ − V V versus angle from the leading edge...

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AAE 334, Fall 2011, Homework 3 Due Monday, August 29 at the beginning of class. Consider a pressure distribution near a leading edge of a symmetric airfoil. We will do this with the flow shown in Figure 3.22 of the text and solved on page 248. We will use and . 1 = V 1 . 0 = Λ 1. Plot the airfoil shape near the leading edge. Hints: a. define an angular position vector for points on the body: thbody = (0.2:0.01:1.8)*pi; % Theta coordinate (remember that thbody=0 is the x -axis, not the leading edge.) b. compute for radial coordinate of points on the body c. compute (x,y) from (r, θ ) , and plot with plot( ) d. to set the correct aspect ratio in your plot, use: set(gca, 'DataAspectRatio' ,[1 1 1]) after the plot command. 2. Compute and plot separately a non-dimensional quantity
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Unformatted text preview: 2 2 1 ∞ − V V versus angle from the leading edge. Top and bottom surfaces in this symmetric flow will have the same result so expect to see only one curve in this plot. This 2 2 1 ∞ − V V quantity is another mathematically correct formula for pressure coefficient ( ) 2 2 1 ∞ ∞ ∞ − = V p p c p ρ in an incompressible flow. 3. Where is there a favorable pressure gradient for the flow on the surface? That is, flow from higher pressure into lower pressure? 4. 2 points extra credit – create a plot showing the pressure coefficient plotted, in some illustrative and useful manner, on the surface of the airfoil. Hand in hard copies of your m-file, plots, and hand-written answer to #3...
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