内置隔板和前缘喷流对机翼油箱热防护的影响  

Effect of built-in partition board and front edge jet on thermal protection of wing tank

作　　者：赵璇 孙智[1] 孙建红[1] Zhao Xuan;Sun Zhi;Sun Jianhong(Key Laboratory of Aircraft Environment Control and Life Support of Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学飞行器环境控制与生命保障工业和信息化部重点实验室

出　　处：《南京理工大学学报》2019年第6期784-792,共9页Journal of Nanjing University of Science and Technology

基　　金：江苏高校优势学科建设工程

摘　　要：为了研究飞机在超声速巡航状态下的气动热效果及对机翼进行相应的热防护设计,该文分析了内置隔板和前缘反向喷流2种不同热防护的防热效果。采用Spalart-Allmaras(SA)湍流模型求解Navier-Stokes方程,对NACA23012翼型在不同马赫数下的气动加热进行了数值分析,并对机翼油箱的热防护进行了研究。结果表明:2种热防护的降温及防热效果均会随来流马赫数的增加而增强;翼型的不对称性会导致上下翼面流场特性的不同,从而产生上下翼面热防护特性的明显差异;当来流马赫数较大时,在降低机翼表面温度及油箱热负荷方面,喷流作为主动式热防护的防热效果要明显优于被动式隔板热防护的防热效果;当来流马赫数为3.0,喷流流量为0.0018 m 3/s时,机翼下翼面平均温度可降低约46.7%。In order to study the aerodynamic thermal effect of an aircraft in supersonic cruise state and the thermal protection design of the wings,the anti-thermal protection effect of the two thermal protections of a built-in partition board and a front edge jet is analyzed.The Spalart-Allmaras(SA)turbulence model is used to solve the Navier-Stokes equation,and the aerodynamic heating of NACA23012 airfoil with different Mach numbers is analyzed numerically,and the thermal protection of the wing tank is studied.The results show that the cooling effect and the anti-thermal protection effect of the two thermal protections increase with the increasing of the inlet Mach number;the asymmetry of the airfoil results in different flow field characteristics of the upper and lower airfoil and significant differences in the thermal protection characteristics;when the inlet Mach number is big,the thermal effect of the jet as an active thermal protection is significantly better than that of the passive board thermal protection in terms of reducing the surface temperature of the wing and the thermal load of the tank;when the inlet Mach number is 3.0,and the jet flow rate is 0.0018 m 3/s,the average temperature of the jet on the lower wing is reduced by about 46.7%.

关 键 词：内置隔板 前缘喷流 机翼 油箱 热防护 超声速 气动加热 

分 类 号：V244.1[航空宇航科学与技术—飞行器设计]