摘要
通过求解可压缩雷诺平均N-S方程(RANS)和S-A湍流模型,数值模拟了菱形翼型在超音速情况下的流动,并对在超音速飞行中襟翼偏转产生的激波-边界层干扰现象进行了分析和比较。计算得到的压力系数与理论计算的结果比较吻合,力矩系数也符合理论分析的结果。
The interaction between shock wave and boundary layer for a diamond aerofoil is studied. The Spalart -Allmaras turbulence model is basically used with the Reynolds-averaged Navier-Stokes equations. It is found that the pressure coefficient can be reasonably consistent with the exact analytical results when the flap angle is small and the moment coefficient can be reasonably predicted by the theory. When the flap angle is large, a seperation region occurred at the convex, and the moment is somehow loss which means that the efficiency of the flap is depressed.
出处
《科学技术与工程》
2007年第11期2727-2730,2744,共5页
Science Technology and Engineering
关键词
超音速
菱形翼型
激波-边界层干扰
supersonic diamond aerofoil shock wave-boundary layer interaction
