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Fluent giving correct values for Cd but incorrect values for Cl

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April 26, 2021, 23:10	Fluent giving correct values for Cd but incorrect values for Cl	#1
Aarib New Member Aarib Irfan Join Date: Mar 2020 Posts: 18 Rep Power: 6	I'm trying to simulate the flow over a 2D airfoil in Fluent. The solver is steady with k-omega SST model. At different angles of attack, the value of Cd i get is always correct but value of CL is always half the value calculated from experimental results. I have set Cl and Cd force vectors correctly and reference area is set to 1 as chord length is 1m. Can someone tell me where can the fault be?

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airfoil, drag coefficients, fluent, lift coefficient

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