Has anyone conducted CFD validation for the Onera M6 wing in HyperWorks CFD, specifically focusing on meshing techniques and the generation of boundary layer meshes with suitable y+ values? If so, could you please share any tutorials or resources rel
I'm trying to conduct CFD validation for the Onera M6 wing in HyperWorks CFD. Specifically, I'm interested in meshing techniques and generating boundary layer meshes with suitable y+ values. I aim to calculate the Coefficient of Lift, Drag, and Pressure distribution. Additionally, I came across this NASA link (https://www.grc.nasa.gov/www/wind/valid/m6wing/m6wing.html), which provides valuable data on the Onera M6 wing. Any insights, tutorials, or resources related to these aspects would be greatly appreciated.
I've attempted the tutorial provided in this link (https://2022.help.altair.com/2022.2/hwcfdsolvers/acusolve/topics/tutorials/acu/acu_2100_intro_cfd_r.htm#ariaid-title21), but unfortunately, it hasn't yielded the desired results for my specific case.
Answers
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You may want to review these two validation cases:
https://help.altair.com/hwcfdsolvers/acusolve/topics/acusolve/turbulent_flow_over_a_naca_airfoil_3.htm
https://help.altair.com/hwcfdsolvers/acusolve/topics/acusolve/laminar_to_turbulent_transition_over_an_airfoil_2.htmThey don't go specifically into the meshing parameters, but you can look at the models, etc. You'll probably want Y+ in the 1 to 10 range.
If you go above Ma 0.3 or so, you'll probably need to go to a variable density model - isentropic being a function of absolute pressure. Be aware that the solver really isn't tested or qualified for external transonic/supersonic flows with shocks, so your experience may vary. But you should be fine to maximum Mach 0.7 or so, using variable density.
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Thank you for the quick response!
The provided link outlines the boundary conditions for the Onera wing and presents a method for only calculating the pressure coefficient (Cp) for a 3D wing, using the Onera wing as an example. While it doesn't have a full tutorial, it still offers valuable insights into the process. This suggests a potential capability to simulate Mach numbers above 0.8 for similar cases.
The specified operating conditions of Onera M6 wing
- Reynolds number (Re): 11.72 x 10^6
- Mach number (Ma): 0.8395
- Angle-of-attack: 3.06 degrees
- Turbulence model: Spalart–Allmaras
- Study air: Ideal Gas
- Temperature: 300 K
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