流向涡与斜激波相互作用的试验研究和数值模拟

Experimental and computational study of vortex/oblique shock interaction

为研究流向涡与斜激波相互作用在超声速燃烧中的应用,进行了由翼产生的流向涡与楔块产生的二维斜激波相互作用的燃烧室冷流试验研究.在不同激波强度下,纹影仪捕捉到了强、中、弱不同的涡/波作用现象.仿真与试验结果符合得较好.试验结果表明:对马赫数为2.3流场,在翼攻角10°时,能产生强流向涡,此工况下,锲角越大,涡/波作用越强.仿真结果表明:马赫数对涡/波作用影响较大,总压影响不明显,总温可影响亚声速回流区的尺寸.

An experimental study of the interaction between supersonic streamwise vortex and two-dimensional oblique shock was conducted to investigate the application of vortex/oblique shock interaction in supersonic combustion.The strong/moderate/weak interactions at different shock strengths were observed in the experiment using color-schlieren method.The numberical results agree with the experiments.Experimental results show that,for the case of Ma=2.3,10 degrees wing attack angle,vortex is strong,and as wedge compress angle increases the vortex/oblique shock interaction changes from weak to strong interaction.Numberical results indicate that for the same wing and wedge situation,Mach number has strong influence on vortex/shock wave interaction.Total temperature can affect the size of the bubble shock.The effect of total pressure is neglectable.