[Aurélien]

Dear Fluent users,

I am currently studying the supercritical airfoil VA-2 with Fluent in order to compare the results with some experimental data (drag coefficient, pressure distribution).

However I have some big differences between my results and the experimental data.
For my study, I am using:
- Spalart-Allmaras viscous model
- Pressure based solver
- M=0.75
- angle of attack = 0.6°
- Reynolds number = 6 millions

My main worry is about the turbulent inlet I have to put in the boundary conditions (pressure far-field).
When I am using the Turbulent intensity and Hydraulic diameter (I have found the values of the wind tunnel) I get a drag coefficient of 0.0205 instead of 0.0101.
When I am usins Turbulent intensity and Turbulent length scale, I get a drag coefficient of 0.0134.

I don't know how to explain this difference particularly for the first one.

Moreover when I am looking at my pressure distribution, I get a weak shock and I am not supposed to get one according to experimental data.


I hope it is enough clear as I am non-native English speaker.
If you need any other information or graph, ask me!!

Aurélien

[sh.d]

hi
I am searching for experimental data for supercritical airfoil.can you send me your data?

[Amar Fayyad]

Hi,

Since the Mach Number you deal is 0.75 over a super-critical aerofoil such as VA 2, you should be considering density based solver rather than pressure based solver in order to accommodate compressibility effects.

[wangshunshun@nudt.edu.cn]

I want to have VA-2 airfoil geometry data.