An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition

Liu Yuan; Qian Zhansen; Xiang Xianhong

doi:10.11729/syltlx20190007

Volume 33 Issue 5

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Journal of Experiments in Fluid Mechanics > 2019 > 33(5): 18-27. > DOI: 10.11729/syltlx20190007

Liu Yuan, Qian Zhansen, Xiang Xianhong. An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(5): 18-27. DOI: 10.11729/syltlx20190007

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An analysis on typical influencing factors of wind tunnel experimental model of over-under TBCC inlet mode transition

Liu Yuan^{1, 2,},
Qian Zhansen^{1, 2, ,},
Xiang Xianhong^{1, 2}

1.
AVIC Aerodynamics Research Institude, Shenyang 110034, China
2.
Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research, Shenyang 110034, China

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Received Date: January 02, 2019
Revised Date: September 03, 2019

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Abstract

Abstract

The aerodynamic performance of a typical over-under TBCC inlet mode transition model has been studied by wind tunnel experiments, and the CFD methods used have also been verified. In the present work, the influence of three typical factors on the experiment is studied by the CFD method, including the side gap, the leading edge bluntness and the forward step on the inner surface. The research results show that the gap between the splitter and the side plate leads to flow spillage between the high and low speed channels. When the gap width reaches 0.5 mm, the total pressure recovery coefficient of the high speed channel is increased by 2.13%, while the flow coefficient is improved by 2.27%. This already has an impact on the aerodynamic performance evaluation of the inlet so that the gap of the model plate should be less than 0.5 mm.The blunted radius of the leading edge has little influence on the aerodynamic performance of the inlet. For the general machining accuracy (0.3 mm), the inlet performance remains basically unchanged. For the general assembly accuracy (0.5 mm), the forward step has very little influence on the inlet flow coefficient, and the total pressure recovery coefficient of the inlet is decreased by 0.44%, which can satisfy the requirements of aerodynamic performance evaluation of the TBCC inlet.
- TBCC inlet,
- wind tunnel experimental model,
- side gap,
- leading edge bluntness,
- upwind step

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