Comparison of experimental and CFD results for the VA-2 supercritical airfoil
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 |
hi
I am searching for experimental data for supercritical airfoil.can you send me your data? |
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. |
Help
I want to have VA-2 airfoil geometry data.
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