An integration method based on a novel combined flow for aerodynamic configuration of strutjet engine  

作　　者：Longsheng XUE Chuan CHENG Chengpeng WANG Keming CHENG 

机构地区：[1]College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China [2]Key Laboratory of Unsteady Aerodynamics and Flow Control,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China [3]Aerospace System Engineering Shanghai,Shanghai 201100,China

出　　处：《Chinese Journal of Aeronautics》2021年第9期156-167,共12页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(Nos.12072157,51776096);China Postdoctoral Science Foundation(Nos.2019TQ0147,2020M671472)。

摘　　要：In this paper a novel design method of aerodynamic configuration is proposed to integrate forebody,strut and inlet for strutjet engine,and a model at design point of Mach number6 is generated to investigate the aerodynamic performance by both simulations and experiments.The basic flow field employed by proposed method is a combined flow named IBB,which is combined by Internal Conical Flow A(ICFA),truncated Busemann flow I(BI)for external section,and truncated Busemann flow II(BII)for internal section.The model configuration is generated by streamline tracing method from basic flow field,in which the forebody section is traced from ICFA and BI flows,and the inlet as well as strut section is traced from BII flow.The simulations in Mach number 4,5,and 6 demonstrate uniform starting flow fields with relatively high total pressure recovery,which agree well with experiments in wind tunnel.Additionally,in low Mach number cases,this inlet could start at Mach number 3 while it is unstarted at Mach number 2.7;in high Mach number cases,a uniform flow could still exist in Mach number 6.5 while a relatively strong shock wave boundary layer interaction is found in cowl area of Mach number 7 case,indicating the inlet designed by proposed method works in a relatively wide Mach number range.

关 键 词：Airframe-propulsion integration Busemann flow Combined flow Hypersonics Wind tunnel test 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]