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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2023, Vol. 44 ›› Issue (2): 626952-626952.doi: 10.7527/S1000-6893.2022.26952

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Wind tunnel test techniques for exhaust nozzle plume effects on near-field sonic boom

Zhongchen LIU1,2,3, Zhansen QIAN1,2,3(), Xuefei LI1,2,3, Yan LENG1,2,3, Dapeng GUO1,3   

  1. 1.AVIC Aerodynamics Research Institute,Shenyang 110034,China
    2.Key Laboratory of Hypersonic Aerodynamic Force and Heat Technology,AVIC Aerodynamics Research Institute,Shenyang 110034,China
    3.Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research,AVIC Aerodynamics Research Institute,Shenyang 110034,China
  • Received:2022-01-14 Revised:2022-02-25 Accepted:2022-03-14 Online:2023-01-25 Published:2022-03-22
  • Contact: Zhansen QIAN E-mail:qianzs@avicari.com.cn
  • Supported by:
    National Natural Science Foundation of China(11672280)

Abstract:

The sonic boom caused by supersonic flight is a key technical problem hindering the development of a new generation of environmentally friendly supersonic airliners. The exhaust nozzle plume has an important effect on the sonic boom characteristics of the whole aircraft, particularly the rear shock characteristics. We design the single nozzle test model with jet and sonic boom test setup, and evaluate the effects of the reflected shock wave from the tunnel wall on the near-field pressure measurement of the model in the wind tunnel test section. The ventilation strut interference on the nozzle plume is analyzed and optimized. Based on the FL-60 wind tunnel of AVIC Aerodynamics Research Institute, the test techniques for the exhaust nozzle plume effects on the near-field sonic boom characteristics of the axisymmetric nozzle model are researched. The test free stream Mach number is 2.0, and the Nozzle Pressure Ratio (NPR) ranges from 1 to 20.39. The test results demonstrate that the comprehensive optimization of the free stream Mach number, the shape of the ventilation strut, the length of the axisymmetric nozzle model, and the relative position between the ventilation strut and the model eliminates the effect of the ventilation strut interference on the nozzle plume, ensuring that the near-field pressure measurement of the model in the confined space of the wind tunnel test section is not affected by the reflected shock wave from the tunnel wall and the ventilation strut. The nozzle plume mainly affects the near-field pressure signatures at the tail of the model. When the free stream Mach number is constant, the nozzle lip shock wave gradually increases and moves to the upstream with the NPR increasing and the nozzle exhaust flow changing from over-expansion to under-expansion, thereby effectively suppressing the development of the nozzle boat-tail expansion wave.

Key words: sonic boom, nozzle plume, nozzle pressure ratio, strut interference, wind tunnel test

CLC Number: