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结合计算流体力学和遗传算法,建立了一种高超声速曲面压缩进气道的反设计方法。根据压力分布反设计了压缩型面。结果表明,该曲面压力分布与目标压力分布符合良好,从而验证了反设计方法的正确性。采用此反设计方法,设计了某高超声速曲面压缩进气道,并和等熵压缩二维进气道进行了比较。研究发现,在其它性能参数几乎相等情况下,曲面压缩进气道总压恢复较等熵压缩基准进气道提高9.7%,长度缩短5.6%。吞入23mm前体附面层后,基准进气道不起动,而曲面压缩进气道总压恢复系数仅下降5.4%,表现出良好的吞附面层能力。
Combining computational fluid dynamics (CFD) and genetic algorithm (GA), an inverse design method of hypersonic surface compression inlet was established. According to the pressure distribution of the anti-compression design of the surface. The results show that the surface pressure distribution is in good agreement with the target pressure distribution, which verifies the correctness of the inverse design method. Using this inverse design method, a hypersonic surface compression inlet was designed and compared with isentropic compression two-dimensional inlet. The study found that, with other performance parameters being almost equal, the total pressure recovery of curved inlet increased by 9.7% and the length by 5.6% compared with that of isentropic compression. After swallowing the 23mm precursor overburden, the baseline inlet did not start and the total pressure recovery factor of the surface compressed inlet decreased by only 5.4%, showing good ability to swallow the surface layer.