NACA埋入式进气口气动特性试验设计优化  

DoE Optimization Design for Aerodynamic Performance of NACA Air Intake

作　　者：朱德轩[1] 杨旸 余志健 李志鹏 张冬 ZHU De-xuan;YANG Yang;YU Zhi-jian;LI Zhi-peng;ZHANG Dong(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China;Nanjing Institute of Future Energy System,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Nanjing 210000,China;Advanced Gas Turbine Laboratory,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201210 [2]中国科学院工程热物理研究所南京未来能源系统研究院,南京210000 [3]中国科学院工程热物理研究所先进燃气轮机实验室,北京100190

出　　处：《科学技术与工程》2021年第17期7355-7362,共8页Science Technology and Engineering

摘　　要：为了优化(美国)国家航空咨询委员会(National Advisory Committee for Aeronautics,NACA)埋入式进气口气动特性,基于计算流体力学(computational fluid dynamics,CFD)数值方法,以阻力、总压恢复系数、出口质量流量和出口马赫数为性能指标,对3个关键几何参数进行了试验设计(design of experiments,DoE)。基准工况结果表明,在进气口斜坡侧边靠近主流处有轴向涡产生。DoE结果表明,斜坡角度对性能指标影响大,斜坡扩张角角影响小,出口转折半径对阻力和出口质量流量影响大,且斜坡角度一定时折转半径越小越好。斜坡角度越小,前缘位置马赫数越小,涡管越长,同一截面速度分布越均匀,因此总压恢复系数和出口质量流量越大,且出口气流不均匀度小,气动性能佳。The design of experiments(DoE)design combined with numerical simulations was employed to optimize the aerodynamic characteristics of a National Advisory Committee for Aeronautics(NACA)air intake.The drag force,total pressure recovery coefficient,mass flow rate and Mach number at the outlet were used to evaluate the performance.Three critical geometric parameters were considered as variables.Results of the baseline case indicated that axial vortexes are formed near the side edge close to the ramp wall.DoE analysis indicated that above four parameters are severely influenced by the ramp angle,while the ramp divergence angle has an opposite effect.A small radius of the turning channel is beneficial to enhance the pressure recovery coefficient and mass flow rate.Mach number at the outlet declines and the velocity uniformity at a certain section increases with decreasing ramp angle value.Meanwhile,larger total pressure recovery coefficient,mass flow rate and vortex tube length are acquired.Thus the aerodynamic performance of the air intake can be improved.

关 键 词：NACA进气口 DoE优化设计 方差分析 气动特性 

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]