亚声速进气道设计敏感参数仿真分析  

Analysis on Simulation of Sensitive Parameters for Subsonic Air Intake

作　　者：曾平君 胡志东 胡杨 肖毅 

机构地区：[1]中航工业洪都,江西南昌330024

出　　处：《教练机》2015年第1期50-55,共6页Trainer

摘　　要：对不同气动布局的两种亚声速进气道建模,并针对两种进气道的敏感参数进行分析。通过对背部双发布局飞机进气道的隔道高度和喉道设计马赫数参数的研究可知,隔道高度增大或者喉道设计马赫数减小,使得进气道出口总压恢复系数增大,增量约0.5%。而对背部单发复杂形状进口(M型进口)布局飞机进气道的喉道形状研究显示,喉道形状越接近进口形状,进气道性能越好,较其他喉道形状进气道,M型喉道进气道出口总压恢复系数最高,最大增量约为1.5%。In this paper, two air intakes in different aerodynamic layouts are designed, and sensitive parameters of those air intakes arc analyzed. According to the rcseareh on partition layer height of the air intake and Much number of the throat for aircraft with configuration of dual-cngine on its back, it is known that the total pressure recovery coefficient of the air intake increases for about 0.5% with the increment of height of partition layer or decrement of throat design Much number. According to the research on shape of the air intake throat of the aircraft with configuration of single engine and complicated air intake shape （M-shaped air intake）, it is found that tile performance of the air intake is better if the throat shape is more similar to that of the intake. Compared to the air intake with throat in other shape, the total pressure recovery coefficient of air intake with throat in M shape is the highest of max. increment about 1.5%.

关 键 词：敏感参数 隔道高度 喉道设计马赫数 喉道形状 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]