外并联式TBCC进气道模态转换风洞试验及模型典型影响因素分析  

An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition

作　　者：刘愿[1,2] 钱战森 向先宏[1,2] Liu Yuan;Qian Zhansen;Xiang Xianhong(AVIC Aerodynamics Research Institude,Shenyang110034,China;Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research,Shenyang110034,China)

机构地区：[1]中国航空工业空气动力研究院,沈阳110034 [2]高速高雷诺数气动力航空科技重点实验室,沈阳110034

出　　处：《实验流体力学》2019年第5期18-27,共10页Journal of Experiments in Fluid Mechanics

基　　金：航空科学基金项目(2017ZA27005)

摘　　要：开展了外并联式TBCC进气道典型模态转换条件下的气动特性风洞试验研究,获得了其主要气动性能参数,并验证了所采用的CFD方法的基本可靠性。以CFD为主要手段,针对该TBCC进气道模型开展了侧板缝隙、前缘钝化以及内型面迎风台阶3方面加工偏差对进气道气动性能影响的研究。结果显示:分流板与侧板之间的缝隙导致了高、低速通道之间的窜流,在缝隙为0.5mm时,高速通道总压恢复系数增加量可达2.13%,同时流量系数增加2.27%,这对进气道气动性能的评估产生了影响,模型侧板缝隙应小于0.5mm;在一般加工精度(0.3mm)下,前缘钝化半径对进气道气动性能的影响较小,进气道性能参数基本保持不变;在一般装配精度(0.5mm)下,内型面迎风台阶对进气道流量系数基本无影响,进气道总压恢复系数的减小量小于0.44%,能够满足进气道气动性能的评估要求。The aerodynamic performance of a typical over-under TBCC inlet mode transition model has been studied by wind tunnel experiments,and the CFD methods used have also been verified.In the present work,the influence of three typical factors on the experiment is studied by the CFD method,including the side gap,the leading edge bluntness and the forward step on the inner surface.The research results show that the gap between the splitter and the side plate leads to flow spillage between the high and low speed channels.When the gap width reaches 0.5 mm,the total pressure recovery coefficient of the high speed channel is increased by 2.13%,while the flow coefficient is improved by 2.27%.This already has an impact on the aerodynamic performance evaluation of the inlet so that the gap of the model plate should be less than 0.5 mm.The blunted radius of the leading edge has little influence on the aerodynamic performance of the inlet.For the general machining accuracy(0.3 mm),the inlet performance remains basically unchanged.For the general assembly accuracy(0.5 mm),the forward step has very little influence on the inlet flow coefficient,and the total pressure recovery coefficient of the inlet is decreased by 0.44%,which can satisfy the requirements of aerodynamic performance evaluation of the TBCC inlet.

关 键 词：TBCC进气道 风洞试验模型 侧板缝隙 前缘钝化 迎风台阶 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]