p9.117_solution - FLOWLAB SOLUTION 9.117 Use the clarky...

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FLOWLAB SOLUTION 9.117 Use the clarky template in FlowLab to investigate changes in the pressure distribution on an airfoil as a function of the angle of attack, α . Assume the flow to be incompressible and inviscid with a free stream Mach number of Ma = 0.15. Run simulations for angles of attack of α = 0 ° , 5 ° , and 10 ° . Plot values of the pressure coefficient, C p = p /( ρU 2 /2), for the upper and lower surfaces for all three cases. Discuss the changes in the pressure on the upper and lower surfaces of the airfoil as α increases. Problem Setup For this problem, the default geometry from FlowLab was used: An approximate flight altitude of 10,000 ft. was used for the ambient conditions. The Mach number was set according to the problem statement and the angle of attack was varied. The flow was set to inviscid for this problem. For all simulation results presented below, the medium mesh resolution was used in FlowLab. An example of this mesh is shown in the following figure.
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p9.117_solution - FLOWLAB SOLUTION 9.117 Use the clarky...

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