变马赫数条件下进气道边界层吹除法数值模拟

推进技术 ›› 2013, Vol. 34 ›› Issue (10): 1310-1315.

变马赫数条件下进气道边界层吹除法数值模拟

丁晨¹,刘猛¹,张继华²,王浚¹

北京航空航天大学航空科学与工程学院,北京 100191;北京航空航天大学航空科学与工程学院,北京 100191;吉林白城63853部队,吉林白城 137001;北京航空航天大学航空科学与工程学院,北京 100191

发布日期:2021-08-15
作者简介:丁晨(1989—)男,博士生,研究领域为超声速进气道优化设计、强化换热技术等。E-mail:dingchenbuaa@163.com
基金资助:
北京航空航天大学研究生科技创新实践基金(YCSJ-01-201207)。

Numerical Simulation on Blowing Method for Controlling Boundary Layer Interaction in Supersonic Inlet at Different Mach Number

School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Unit 63853in Bai Cheng, Bai Cheng 137001, China;School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 为了对超声速进气道内激波/边界层干扰控制进行研究,将进气道简化为平板/楔形体结构,用数值方法研究一段包线上吹除法抑制气流分离的性能变化趋势以及吹除气体总压、喷嘴高度对吹除性能的影响。研究表明,吹除法在一定马赫数范围内能抑制气流分离,马赫数超过设计点后,随着马赫数增大吹除性能降低。达到吹除效果后增大吹除压力和增加喷嘴高度不能提高吹除性能。随着来流马赫数增大,气流抗反压能力增强,气流分离减少。 

关键词: 超声速进气道;激波/边界层干扰控制;吹除法;变马赫数;数值仿真 

Abstract: In order to study the shock wave/boundary layer interaction control, two-dimensional flat/wedge structure was used to simplify supersonic inlet, and numerical simulation method was used to study the tendency of blowing effect under different flow Mach number. Furthermore, the effects of the blowing total gas pressure, blowing nozzle height and other parameters on the inhibition of boundary layer airflow separation were discussed. Results show that the blowing method can effectively inhibit the flow separation under a range of flow Mach number, and when the flow condition deviates from the design point, the performance of the blowing method degrades as the increase of Mach number. Increasing the blowing pressure or the blowing nozzle height cannot improve the effect of blowing.With increasing the flow Mach number the flow anti pressure ability is enhanced, and flow separation is reduced.

Key words: Supersonic inlet; Control of shock /boundary layer interaction; Blowing method; Different flow Mach number; Numerical simulation

丁晨,刘猛,张继华,王浚. 变马赫数条件下进气道边界层吹除法数值模拟[J]. 推进技术, 2013, 34(10): 1310-1315.

DING Chen¹,LIU Meng¹,ZHANG Ji-hua²,WANG Jun¹. Numerical Simulation on Blowing Method for Controlling Boundary Layer Interaction in Supersonic Inlet at Different Mach Number[J]. Journal of Propulsion Technology, 2013, 34(10): 1310-1315.

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