带逆向喷流激波针非设计点减阻防热性能研究  

Research on drag and heat flux reduction of combination of spike and forward-facing jet in off-design regimes

作　　者：何天琦 罗世彬 HE Tian-qi;LUO Shi-bin(School of Aeronautics and Astronautics,University of Central South,Changsha 410083,China)

机构地区：[1]中南大学航空航天学院

出　　处：《飞行力学》2019年第6期46-50,共5页Flight Dynamics

摘　　要：为了研究带逆向喷流激波针在非设计点状态下对钝头体的减阻防热性能,采用有限体积法求解三维Navier-Stokes方程,并选用SST k-ω湍流模型,分别对不同迎角和马赫数下带逆向喷流激波针钝头体的流场进行了数值模拟。仿真结果表明:在0°~6°迎角范围以及不同马赫数下,带逆向喷流激波针均能起到较好的减阻效果,改善了驻点区域热环境,但随着迎角的增大,逆向喷流激波针对钝头体肩部区域的防热能力减弱。In order to research the drag and surface heat flux reduction performance of combination of spike and forward-facing jet to blunt body in off-design regimes,the Navier-Stokes equations are solved by finite volume method based on the SST k-ωturbulent flow model,and the flow field of the blunt body with spike and forward-facing jet under different angle of attack and Mach are numerically simulated.The results show that the spike with forward-facing jet can reduce drag and improve the thermal environment in the standing point area at the AOA from 0 to 6 degrees and under different flight Mach numbers,but with the increase of AOA,the anti-thermal ability of the spike with forward-facing jet against the shoulder area of blunt body is weakened.

关 键 词：高超声速 逆向喷流 激波针 减阻防热 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]