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unsteady values of Cl and CD in steady state condition
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hello everyone
how u doin Im having problem in getting steady CL and Cd values over a modified wing. the value of CL range in about 0.9 to 1.4. Im running a steady state solution with transition sst turbulence model with simple solver under in-compressible and constant viscous air flow. i made a structured mesh in ICEM with a 2.1M mesh elements.any advice. Attachment 70003 |
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