COMPUTATIONAL ANALYSES OF SUPERSONIC FLOWS OVER A DELTA WING AT HIGH ANGLES OF ATTACK
COMPUTATIONAL ANALYSES OF SUPERSONIC FLOWS OVER A DELTA WING AT HIGH ANGLES OF ATTACK
复制标题
高迎角三角翼上超音速流动的计算分析
DOI：
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发表时间：
2006
期刊：
影响因子：
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通讯作者：
A. Oyama
中科院分区：
文献类型：
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作者：
Genta Imai;K. Fujii;A. Oyama
本文计算研究了65 °尖前缘后掠三角翼大迎角超音速绕流。不同自由飞行马赫数的计算模拟表明，在自由飞行马赫数为0.8和1.2之间，流场有一个突变。不同流动条件下模拟结果的可视化图像表明，当前缘马赫数变为超音速时，来自前缘的膨胀波加速流动并使共享层更靠近表面时，会发生这种非线性行为。结果还表明，在自由流马赫数为1.0以下和以上，气动特性有不同的趋势。突变并不发生在前人研究提出的分类边界上。当来流马赫数达到超声速时，三维流动结构中的主涡、涡破裂和迎风流等成分具有不同的性质，导致气动特性呈现非线性行为。
Supersonic flows over a 65-degrees sweep delta wing with a sharp leading edge at high angles of attack are computationally studied. Computational simulations with various freestream Mach numbers show that there is a sudden change in flow fields between the freestream Mach number of 0.8 and 1.2. Visualized images of the simulation results at different flow conditions show that this nonlinear behavior occurs as expansion waves from the leading edge accelerate the flow and shift the share layer closer to the surface when the Mach number at the leading edge becomes supersonic. The results also show that aerodynamic characteristics have a different trend below and above the free-stream Mach number of 1.0. The sudden change occurs not at the boundary of the classification proposed by the former studies. When the free-stream Mach number becomes supersonic, components of the threedimensional flow structure such as primary vortex, vortex breakdown and windward flow have different nature, which lead to the nonlinear behavior of aerodynamic characteristics.