一种超声速民机低声爆高效气动布局风洞试验

doi:10.7527/S1000-6893.2025.31941

Abstract

Abstract:

Wide speed range， low sonic boom and high efficiency aerodynamic layout design and wind tunnel test method is one of the most important key technologies and difficulties for supersonic civil aircraft. First， the high-speed force measurement and sonic boom wind tunnel test models of an advanced low sonic boom supersonic civil aircraft aerodynamic layout are proposed. The layout are designed and processed by using the methods of anti-design of sonic boom minimization theory and the mixed credibility anti-design method based on the parameterized near-field overpressure signal and the aft-body design based on wave system beneficial interference. Then， due to large gas consumption of sonic boom wind tunnel test and relatively high quality requirement of wind tunnel flow field， a non-reflective pressure gauge is designed and the spatial average technique is developed to reduce the measurement error caused by the non-uniform disturbance of the background flow field. Finally， the sonic boom and high-speed force wind tunnel test are carried out for the low sonic boom aerodynamic layout of the proposed supersonic civil aircraft， and the high-quality sonic boom and force test data are obtained. The results shows that the proposed method for aerodynamic layout design and wind tunnel test of the supersonic civil aircraft can obtain better boom reduction effect and relatively high test precision， and have application value for such aircraft design. The test results of high-speed force measurement and boom sonic test are in good agreement with those obtained by CFD method， and the rationality of the developed aerodynamic layout design and wind tunnel test method for supersonic civil aircraft is verified. The research work has certain engineering guiding values for aerodynamic layout design and wind tunnel test of supersonic civil aircraft.

Key words: supersonic civil aircraft, wind tunnel test, sonic boom, aerodynamic layout, spatial average, aerodynamic force, measurement error

CLC Number:

V211

Wei WANG, Junfu LI, Fengxue QIAN, Yuting TAN, Yan ZHAO, Bowen ZHAO, Qing CHEN, Ke SONG. Wind tunnel test of low sonic boom high efficiency layout for supersonic civil aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(20): 531941.

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Wind tunnel test of low sonic boom high efficiency layout for supersonic civil aircraft

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