吸气式高超声速飞行器内外流同时测力试验

doi:10.7527/S1000-6893.2014.0123

Abstract

Abstract:

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.

Key words: hypersonic vehicle, wind tunnel test, aerodynamic, model design, inlet, internal and external flow decoupling

CLC Number:

WANG Zejiang, SUN Peng, LI Xuguo, TANG Xiaowei. Force test on internal and external flow simultaneous measurement of air-breathing hypersonic vehicle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(3): 797-803.

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

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