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unsteady values of cl and cd in steady state solution

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Old   May 17, 2019, 12:31
Default unsteady values of cl and cd in steady state solution
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Asfand Yaar Sher
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hello everyone
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. angle of attack is 18 degrees at 2e5 reynolds number with 30 m/s flow
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