Transonic Flow over the ONERA M6 Wing
Application ID: 105731
This example demonstrates how to set up the classical external-flow problem of solving for the high-speed, compressible, turbulent flow over the ONERA-M6 wing. The problem involves finding a steady-state solution of the flow field around the 3D, swept wing geometry, immersed in a transonic flow at a moderately high angle of attack. The solution indicates the formation of weak shocks on the upper surface of the wing.
Disclaimer: This model uses data from the ONERA-M6 wing as a reference. This model is not affiliated with, endorsed by, or sponsored by ONERA.
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