p9.119_solution

p9.119_solution - FLOWLAB SOLUTION 9.119 Use the same...

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9.119 Use the same template as in Problem 9.118 to investigate the effects of altitude, h , (by altering the ambient pressure, p , and temperature, T ) on the aerodynamic forces lift and drag. Set the angle of attack to a constant value of α = 5 ° and run simulations for sea level, h = 0, and h = 20,000 ft while maintaining the same flight speed of U = 200 mph. Calculate the lift and drag forces for both altitudes. Discuss the differences as a result of altitude changes. Problem Setup For this problem, the default geometry from FlowLab was used: The flow was set to Viscous and the Boundary Condition settings were altered to achieve the stated flight conditions. The changes in ambient pressure and temperature are taken from the standard atmosphere (see App. C of the text). Altitude (ft) Pressure(Pa) Temperature (K) Speed of Sound (ft/s) Mach No. 0 101329 288 1117 0.26 20000 46603 248 1037 0.28 For example, the sea level settings are shown below. For all simulations, the medium mesh resolution was used for the grid setup. A sample of
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This note was uploaded on 03/27/2010 for the course ME 330 taught by Professor All during the Spring '08 term at University of Texas.

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p9.119_solution - FLOWLAB SOLUTION 9.119 Use the same...

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