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所属单位：能源与动力学院

发表刊物：Tuijin Jishu

摘要：In order to study the effects of wall roughness on aerodynamic performance of hypersonic inlet, numerical simulation which had been verified and theoretical analysis were carried out. The results indicated that at the same Mach number, as the wall roughness increased, the mass flow coefficient, the total-pressure recovery coefficient and Mach number of inlet's exit all declined while the static pressure ratio, the pressure drag coefficient, the friction drag coefficient and the start Mach number all raised. Under different Mach numbers or blunt radius, the aerodynamic performance of the inlet was similar while the wall roughness changed. Through curve fitting, the relationship between each parameter of aerodynamic performance and wall roughness was presented, so that it can be predicted of the aerodynamic and starting performance of the inlet with rough wall according to the smooth one. For this article, the start Mach number of the inlet increased from 4.25 to 4.85 when the relative roughness increased from 0 to 0.625%. Thicker boundary layer because of the wall roughness was the main reason why the aerodynamic performance of the inlet changed partly. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.

ISSN号：1001-4055

是否译文：否

发表时间：2018-08-01

合写作者：Zhang, Jin-Sheng,Lu, Jie,黄国平

通讯作者：袁化成