Unformatted text preview: 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. Hard copy of plot and m-file should be handed it. cp x o o 10 10 ≤ ≤ − α Be certain to write short sentences with your analysis to explain your work to the grader. Note: If you’ve not learned to use print –dmeta in Matlab, you might find it helpful. This command copies your current figure into the paste buffer. From there you can paste into a Word or PowerPoint document....
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- Fall '09
- Aerodynamics, Airfoil, NACA, lift coefficient, Angle of attack, pitching moment coefficients