超声速进气道唇口剖面形状对飞机升阻比的影响  

Effect of Supersonic Inletlip Profile on Lift-drag Ratio of Aircraft

作　　者：苏嘉殷 李博[1] 童佳慧 邱宇宸 徐猛 SU Jiayin;LI Bo;TONG Jiahui;QIU Yuchen;XU Meng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2023年第4期132-136,共5页Machine Building & Automation

摘　　要：针对一种采用无隔道超声速进气道的超声速靶机,使用数值仿真方法对内外流一体化的全机流场进行数值模拟,研究不同唇口剖面形状对全机升阻比的影响。结果表明:设计状态下不同唇口剖面形状升阻比不同。综合考虑高低速飞行马赫数在0°~6°飞行攻角下,飞机的气动力特性,长短轴比为9∶1的椭圆唇口为最佳唇口剖面形状。Aiming at a supersonic target aircraft with diverterless supersonic inlet,the whole flow field of the integrated internal and external flow was simulated by numerical simulation method,and the effect of different lip profile on lift-drag ratio of the aircraft was studied.The study found that different lip profile could affect the pressure distribution on the lower surface of the wing,furthermore changing the lift of the wing.Based on the aerodynamic characteristics of the aircraft at high and low flight Mach number of 0°—6°flight angle of attack,it can be concluded that the ellipse lip with 9∶1 axial ratio is the optimal lip profile for the aircraft.

关 键 词：无隔道超声速进气道 超声速飞机 唇口 气动力特性 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]