高超声速一体化飞行器冷流状态气动特性研究

采用数值模拟和风洞实验方法，对高超声速一体化飞行器缩比模型在发动机关闭以及发动机通流状态下的气动特性进行研究。实验中采用彩色纹影系统对缩比模型飞行器的超声速流场进行显示，并通过六分量应力天平测得了全机的升力、阻力和俯仰力矩，数值模拟气动力系数以及流场特征与实验结果吻合较好，同时分析了飞行器保持静稳定状态下的质心选择范围。结果表明进气道开启之后飞行器升力阻力以及抬头力矩显著下降，但此飞行器配平迎角仍较大。该实验结果验证了数值方法的可靠性并为飞行器构型设计提供了参考数据。

Aerodynamic characterization of an integrated hypersonic vehicle

An analysis was conducted for the aerodynamic characteristic of two hypersonic in- tegrated vehicle configurations （cowl-closed and cowl-opening） with numerical simulations and wind tunnel tests. The color schlieren techniques were used to visualize supersonic flow about the subscale model vehicle, the lift, drag and pitching moment of the vehicle was measured with a 6- component wind tunnel balance, the CFD predicted results were compared against the experimental data and showed good agreement, and the region of center of mass location was calculated for the analysis of the vehicle longitudinal static stability. These results showed that the act of opening the inlet door resulted in a loss of the lift, drag and nose-down pitch increment, but the trim angle of attack was still too high with no deflection of control surfaces. These results helped build confidence in the CFD tools and provide reference data for the vehicle configuration design.