Abstract: Based on computational fluid dynamics and genetic algorithm,an inverse design method for hypersonic inlet with curved wall compression has been established.The inverse design of a curved wall with certain wall pressure distributions has been explored.The results indicted that the static pressure distributions of the curved wall accord well with the objective pressure distributions,and thus the inverse codes were validated.A hypersonic inlet with curved wall compression was designed with the inverse codes and compared with a two dimensional isentropic hypersonic inlet.Numerical simulations of the two hypersonic inlets showed that,with other performance parameters nearly equal,the total pressure recovery of the new inlet is about 9.7% higher than that of the base inlet,while its total length is about 5.6% shorter than that of the isentropic inlet.With 23 mm boundary layer ingested,the isentropic hypersonic inlet unstarts,while the total pressure recovery of the new inlet just decreases about 5.4%,showing good performance of ingestion boundary layer.

Key words: Hypersonic inlet;Curved wall compression;Inverse design;Genetic algorithm;HLLE scheme

摘要： 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。

关键词: 高超声速进气道;曲面压缩;反设计;遗传算法;HLLE格式