I have been modeling some airfoils to test its aerodynamic properties and when comparing to air tools database the values are very different.
I was expecting the lift coefficient somewhere near 0.6 and I am getting 0.10375 and was expecting drag coefficient near 0.1 and I am getting 0.00505
I am using 20 m/s speed at x-direction only at the inlet boundary condition (velocity inlet) and the outlet as pressure outlet with 0 gauge Pressure. The mesh seems ok since I already did validation tests and the maximum y+ value is 4 (using RNG k-epsilon, the maximum y+ should be less than 5). One thing I noticed is that the dynamic pressure on the upper side of the wing is higher than the lower side. For the absolute pressure, however, on the upper side is shorter than the lower side.
Any idea on where to tackle this problem? Where should I look at?
Please check your reference value from "setup" portion. If these values are not in the tolarable range then pls check your boundary condition.
Besides you can check serially
1. Geometry- please make sure your generated data points were serially connected.
2. Mesh size was accurate or not? (I guess your Y+ value was in the correct range)
3. Please define cell zone condition (if you have any)
4. Please again check your boundary condition.
5. Change your option in "Solution initialization" & "compute from" to see the effect. (Which one you used? Please specify)
6. If possible then lower the number your residuals & increase the number of iteration to see "if" the result will change or not!!
Wish you a good luck
Thank you for the detailed explanation!
I think the error could be on the reference values, I did not change them because I didn't know which values to choose. Can you clarify that?
Do I need to change the length (1m - original) to the airfoil length? I don't understand what these reference values are for
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