The analysis conditions adopt Mach number, angle of attack, and Reynolds number. A comparison of the wing surface pressure coefficient distribution is also conducted.
Using the general-purpose thermal fluid analysis software AICFD, we will conduct a transonic analysis of the M6 wing. The M6 wing is a classical test case for studying transonic flow and is a semi-infinite airfoil designed by the French aerospace research institute ONERA. The M6 wing exhibits typical transonic airfoil characteristics, such as shock waves that appear on the wing under specific conditions and expansion waves behind the shock waves. *For more detailed information, please refer to the related links. For further details, you can download the PDF or feel free to contact us.*
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