hw7 - 16.100 Homework Assignment # 7 Due: Monday, November...

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16.100 Homework Assignment # 7 Due: Monday, November 7, 9am Reading Assignment Anderson, 3 rd edition: Chapter 17, pages 787 – 801 Chapter 18, pages 803 – 810 Problem 1 In this problem, we will use Xfoil to simulate the flow of over an airfoil at relatively low Reynolds number, and compare the results to some simple flat plate results. To run Xfoil, you can use MIT server or download a copy of Xfoil for Windows. In either case, directions are available on the MIT server . a) Using Xfoil, calculate the drag coefficient versus Reynolds number for the NACA 0004 airfoil from to Re at zero degrees angle of attack. Plot the results on a log-log scale and include the drag coefficient from the laminar flat plate solution by Blasius. How does the Xfoil result compare to the flat plate theory? 3 10 1 Re × = 6 10 1 × = b) A form factor approach is often used to estimate the drag on an airfoil (or other body) by multiplying the skin friction drag estimated from flat plate results. Specifically, assume
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hw7 - 16.100 Homework Assignment # 7 Due: Monday, November...

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