曲外锥乘波前体进气道流量测量及实验与仿真对比研究

流量捕获特性是高超声速进气道的重要特性。针对一体化曲外锥乘波前体进气道，开展了流量特性精细测量分析以及实验与仿真对比研究。采用节流实验系统，在来流马赫数3.0、3.5和4.0，迎角-4°至6°和不同进锥位置上，获得了该型前体进气道的流量特性，分析了流量测量均方根误差。开展了来流马赫数4.0、迎角-4°~6°条件下的实验与仿真对比研究。研究结果表明:一体化曲外锥乘波前体进气道构型具有良好的流动捕获能力，在来流马赫数3.5、4.0和6.0以及迎角0°条件下，流量系数分别为0.60、0.68和1.00；在节流实验系统充分壅塞的条件下，流量测量均方根误差在2%以内；仿真所获流量特性随迎角变化的线性度较好，和实验结果的吻合度较高。

Mass flux measurement and comparison study of simulation and experiment on curved cone waverider forebody inlet

The mass flow capture performance is a key characteristic of the integrated Curved Cone Waverider forebody Inlet(CCWI). Delicate mass flow measurement experiment and comparison studies between experiment and simulation are conducted for obtaining the CCWI's mass flow capture ratio. Using the mass flow measurement experimental system, the CCWI's mass flow capture and static pressure distribution are obtained at free stream flow Mach number(Ma_∞)3.0, 3.5 and 4.0, Angle of Attack (AOA) from -4° to 6°。Comparison studies of CFD simulation and experiment are carried out at Ma_∞=4.0, AOA from -4° to 6°。Based on the verified CFD software and simulation methods, the mass flux and compression performance of the CCWI are examined at Ma_∞=4.0 and 6.0. The results show that the average square error of the mass flux measurement is less than 2%. Simulation and experimental results agree well with each other. The CCWI has good flow compression abilities and its mass capture ratios are 0.60, 0.68 and 1.00 at Ma_∞=3.5, 4.0 and 6.0, AOA=0° respectively.