Support interference and correction of cold-flow force test for air-breathing hypersonic vehicle in wind tunnel
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摘要: 吸气式高超声速飞行器整体外形与推进系统性能高度耦合，在风洞测力试验中，支撑机构不可避免会对其气动特性产生影响。针对该类飞行器冷态气动力试验中存在的支撑干扰问题，以基于乘波前体的机体/发动机一体化飞行器为研究对象开展试验和计算研究，对比了尾支撑、背支撑和背支撑+虚拟尾支撑3种风洞支撑机构对飞行器主要气动力参数的影响，并通过比较不同支撑方式的测量结果对气动力进行了校正。试验在来流马赫数4和6两个工况下进行。结果表明：相对于背支撑，尾支撑对飞行器气动力参数的影响较小，更适合作为吸气式高超声速飞行器冷态测力试验的支撑机构；结合背支撑和背支撑+虚拟尾支撑的方式，可以有效地对尾支撑测量结果进行校正，提供更为精准的气动力试验数据。
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关键词:
- 吸气式高超声速飞行器 /
- 冷态测力试验 /
- 支撑干扰 /
- 干扰校正
Abstract: The supporting mechanism greatly influences the aerodynamic force measurement of the air-breathing hypersonic flight vehicles in wind tunnel tests. In this paper, the supporting interference is studied by both wind tunnel experiments and CFD. First, an integrated vehicle is developed based on the wedge-elliptical cone waverider configuration method. Three types of supporting mechanisms are adopted to conduct the force measurement at Mach 4 and 6 in the hypersonic wind tunnel, with the rear sting mount, the back blade mount, and the back blade mount + dummy rear sting mount. And, a correction method is adopted here to account for the supporting interference. With this method, the interference increments due to the supporting mechanism can be eliminated from the results obtained from the rear sting mount. The result shows that all the supporting mechanisms have an influence on the aerodynamic force and the rear sting mount is more suitable to be used as the supporting mechanism with a less influence in contrast with the back blade and the back blade mount + dummy rear sting mount. In addition, it is recommended to use the correction method to improve the measurement accuracy of the experiment data. -
图 3 背支撑+虚拟尾支撑实物图
Figure 3. Physical picture of the back blade + dummy rear sting mount
图 10 尾支撑+虚拟支撑试验流场与计算流场对比(Ma=4，α=0°)
Figure 10. Comparison of flow fields obtained by experiment and CFD when Ma=4, α=0°
图 11 尾支撑试验流场与计算流场对比(Ma=6，α=0°)
Figure 11. Comparison of flow fields obtained by experiment and CFD when Ma=6, α=0°
图 12 Ma=4时升力系数随迎角变化曲线
Figure 12. Curves of lift coefficients with attack angles when Ma=4
图 13 Ma=4时阻力系数随迎角变化曲线
Figure 13. Curves of drag coefficients with attack angles when Ma=4
图 14 Ma=4时升阻比系数随迎角变化曲线
Figure 14. Curves of lift-to-drag ratios with attack angles when Ma=4
图 15 Ma=4时俯仰力矩系数随迎角变化曲线
Figure 15. Curves of moment coefficients with attack angles when Ma=4
图 16 Ma=6时升力系数随迎角变化曲线
Figure 16. Curves of lift coefficients with attack angles when Ma=6
图 17 Ma=6时阻力系数随迎角变化曲线
Figure 17. Curves of drag coefficients with attack angles when Ma=6
图 18 Ma=6时升阻比系数随迎角变化曲线
Figure 18. Curves of lift-to-drag ratios with attack angles when Ma=6
图 19 Ma=6时俯仰力矩系数随迎角变化曲线
Figure 19. Curves of moment coefficients with attack angles when Ma=6
图 20 Ma=4, α=0°时尾支撑和无支撑时模型下表面压力分布对比
Figure 20. Comparison of pressure distributions on the lower surface of the model with rear sting and unsupported when Ma=4, α=0°
图 21 Ma=4, α=0°时背支撑和无支撑时模型上表面压力分布对比
Figure 21. Comparison of pressure distributions on the upper surface of the model with back blade and unsupported when Ma=4, α=0°
表 1 实验条件
Table 1. Flow conditions
Ma p0/MPa T0/℃ Re/m-1 3.970 0.5 25 2.92×107 5.933 2.0 191 1.80×107 
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