吸气式高超声速飞行器内外流同时测力试验

为研究吸气式高超声速飞行器新型测力试验技术的可行性,在马赫数Ma=6、高度H=27km模拟飞行环境下开展了风洞试验。以轴对称吸气式高超声速飞行器无舵翼简化构型为研究对象,通过合理的试验系统设计解决内外流解耦关键技术,采用两个环式六分量天平在同一车次上测量模型内外流气动力载荷。试验结果表明:内外流气动力天平测量数据和全模气动力数据准确反映了内外流解耦、内外流窜流、进气道起动/不起动以及溢流影响等物理现象;从物理上实现了内外流解耦;内流气动力对全机气动性能贡献大;内外流解耦、进气道起动时,气动力数据准确、重复性好;窜流产生的传力属于内力。试验证明,同时测力试验技术可行,为解决内外流气动数据源于不同试验所致的不确定性问题提供了有效手段。

Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle

In order to investigate the new force test technique feasibility of the air-breathing hypersonic vehicle, a wind tunnel test is conducted at the simulated flight environment of Mach number Ma=6.0 and altitude H=27 km. The research subject is a simplified configuration without wings and fins of an axisymmetric air-breathing hypersonic vehicle. The internal and external flow decoupling crucial technology is settled by the rational test system design. The internal and external flow aerodynamic loads of the model in the same run are measured by a double ring type six-component balances. The test results show that the internal and external flow aerodynamic measurements and the total aerodynamic datum exactly reflect abundant physical phenomena, including decoupling and cross-flow between the internal and external flow, the inlet starting/un-starting, and the spillage influence. The internal and external flow decoupling is realized in physics. The internal aerodynamic forces make a great contribution to the hypersonic vehicle aerodynamic performance. Under the conditions of the internal and external flow decoupling, the aerodynamic data have high accuracy and good repeatability when the inlet starts. The forces from cross-flow are the internal forces. The results of the test indicate that it is feasible for this new force test technique to provide a valid method to solve the problem of internal and external flow aerodynamic data uncertainty from different tests.