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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.
In order to study the application of the interaction between the flow vortex and the oblique shock wave in the supersonic combustion, the cold flow experiment of the combustion chamber interacting by the flow vortex generated by the wing and the two-dimensional oblique shock wave generated by the wedge was carried out. Under different shock intensities Under the condition of Mach number is 2.3, the effect of vortex / wave on strong, moderate and weak vortex is captured by the instrument. The simulation results are in good agreement with the experimental results. The vortex / wave effect is stronger under the condition of larger wedge angle.The simulation results show that the Mach number has a great influence on the vortex / wave interaction and the total pressure has no obvious effect on the total pressure, and the total temperature can affect the subsonic backflow Area size.