关键词: 高超声速进气道;曲面压缩;反设计;遗传算法;HLLE格式

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