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Old   July 30, 2014, 03:31
Post Boundary Condition
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RAHUL RAMANUJAM is on a distinguished road
I need to compute the lift and drag coefficients of an airfoil for angle of attack varying from -180 to +180 degree at an interval of 1 degree and for Mach number from .1 to 1. Is there any procedure to automate the procedure ??

Thank you in advance...
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airfoil, angle of attack, boundary condition, udf

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