Experimental and Numerical Research on a Three-Dimensional Inward-Turning Inlet
Publication: Journal of Aerospace Engineering
Volume 36, Issue 3
Abstract
The aerodynamic performance and flow field structure of an inward-turning inlet at a high flying Mach number are attracting more and more attention. The main purpose of this paper is to study the aerodynamic performance and the back pressure characteristics of a circular entrance three-dimensional inward-turning inlet at , with the combination of wind tunnel test and numerical simulation. This series of experiments is divided into three parts to explore the unstart boundary, self-start ability, and suction slots influence. The experimental results show that at design point , the inlet outlet Mach number is 2.29 and the total pressure recovery coefficient is 0.31. Further numerical simulation results indicate that the opening of suction slots could enhance the maximum capability of back pressure about 7.3%. The circumferential flow in the isolator caused the asymmetry of the shock train and led to the nonuniform distribution of the separation region. The different size of the separation zones on the upper wall and the lower wall eventually leads to different pressure distribution.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
This work is supported by the National Natural Science Foundation (No. 11772155) and Postgraduate Research & Practice Innovation Program of Jiangsu Province (No. KYCX18_0313).
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Published In
Journal of Aerospace Engineering
Volume 36 • Issue 3 • May 2023
Copyright
© 2023 American Society of Civil Engineers.
History
Received: Sep 27, 2021
Accepted: Jan 4, 2023
Published online: Feb 21, 2023
Published in print: May 1, 2023
Discussion open until: Jul 21, 2023
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