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July 30, 2014, 04:31 |
Boundary Condition
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#1 |
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RAHUL R
Join Date: Jul 2014
Posts: 1
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Hi,
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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