March 27, 2022 at 3:19 pmsahajthapaSubscriber
I am performing a 2-D simulating flow over NACA 0035 with AoA ranging from 0 to 15 degrees with k-wSST turbulence model and Re=0.139e6. The main problem occurs during computation of lift coefficient. For increasing AoA, the lift coefficient merely increases with the max lift of 0.03, however I am getting correct values for drag coefficient. I am comparing the results with XFOIL. At 6 degrees AOA, XFOIL gives CL of 0.33 however i am getting -0..03. Flow separation occur at 10 degrees AoA.
I rechecked the reference values and the vectors for velocity (cos(), sin()) and lift coefficient (-sin() , cos () ) but cannot find any problem at all.
For your reference,
Turbulence Model: k-w SST
Pressure-Velocity Coupling: SIMPLE
Area+ 0.1016 m
Depth= 1 m (2-D)
Length = 0.1016 m (chord length)
y+ is ensured below 0.8. Number of elements: 23200, C-shaped domain for inlet.
Thank you for your time!!March 28, 2022 at 2:08 pmRobAnsys EmployeeHow well resolved is the streamwise mesh and mesh in the wake region?
March 28, 2022 at 2:17 pmViewing 2 reply threads
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