[Diptaru]

Currently, I am simulating flow over an airfoil 2D steady-state.

turbulence model: k-w sst
Boundary condition: velocity inlet, pressure outlet, wall and airfoil

solver: coupled

chord: 1m
density: 1.184 kg/m^3
viscosity: 1.85*10^-5
velocity: 15.625 m/s
Reynolds number: ~ 1,000,000

I did the grid independence test and tried to validate the CFD results with the Experimental data.

however, the CFD results (lift coefficient) are overshooting or overpredicted compared to the experimental data.

1/What could be the reason behind this?

2/ What would be the possible solution to fix this issue?

for your reference, I am attaching the figures below.

GIT.jpg

Validation.jpg


Note: in GIT plot the triangle markers are the lift coefficient data