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首页> 外文期刊>International Journal of Aerodynamics >Implications of compressibility effects for Reynolds-scaled testing of an inverted wing in ground effect
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Implications of compressibility effects for Reynolds-scaled testing of an inverted wing in ground effect

机译：可压缩性效应对地面反作用翼雷诺尺度试验的影响

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摘要

The influence of compressibility around an isolated inverted wing at a fixed Reynolds number was examined as relevant to the issue of wind tunnel scaling effects. Three-dimensional simulations were conducted for low ground clearances, at: full scale and a Mach number of 0.088, at 50% scale at Mach 0.176, and at 25% scale at Mach 0.352. As the scale was reduced, the increasing peak local Mach number between the wing and the ground resulted in a higher propensity of the flow to separate towards the trailing edge, and for incompressible or full-scale CFD to underestimate the lift and drag coefficients by an ever-increasing margin. The lower vortex path was less affected. The results suggest that compressible CFD of a scale experiment ought to be conducted at the same Reynolds number and Mach number as the tunnel test for the best possible correlation at free-stream Mach numbers beyond 0.15.
机译：研究了与固定雷诺数无关的倒置机翼周围可压缩性的影响，与风洞结垢效应有关。针对低离地间隙进行了三维模拟，其全尺寸和马赫数为0.088，比例为50％时为0.176马赫，比例为25％时为0.352马赫。随着尺度的减小，机翼和地面之间的峰值局部马赫数不断增加，导致气流向后缘分离的倾向更高，而对于不可压缩或全尺度的CFD，则低估了升力和阻力系数。利润不断增加。较低的涡流路径受到的影响较小。结果表明，应在与隧道试验相同的雷诺数和马赫数下进行规模试验的可压缩CFD，以在自由流马赫数超过0.15时获得最佳相关性。

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