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Unformatted text preview: calculate the pressure coefficient. It was witnessed that the angle of attack with which flow separation occurred at increased as the Reynolds number increased. Also once the flow was separated, in order for it to reattach, it required at lower angle of attack at which it separated. The drag coefficient calculated to be 0.012. When comparing the distribution of the pressure coefficient on the top of the airfoil to the bottom, they turned out to be very similar, which is what is expected for at symmetric airfoil at a zero degree angle of attack. For further studies it would be useful to complete the same procedures just at different Reynolds numbers and angles of attack to ultimately know how the NACA 0012 will behave in any flow....
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 Fall '10
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