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Experimental and numerical investigation on a supersonic inlet with large bleed window

Published online by Cambridge University Press:  08 September 2021

HC. Yuan ,
JS. Zhang Open the ORCID record for JS. Zhang [Opens in a new window] ,
YF. Wang  and
GP. Huang
HC. Yuan*
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
JS. Zhang
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
YF. Wang
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
GP. Huang
Affiliation:
College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics, Nanjing210016, China
*
E-mail: [email protected]
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Abstract

The design of a two-dimensional supersonic inlet with large bleed window at low Mach number was developed. Numerical simulation and wind tunnel experiments were carried out to investigate the aerodynamic performance and variable geometric rules of the inlet. The result indicates that the single-degree-of-freedom variable geometry scheme adopted in this paper guarantees the steady work of the inlet over a wide speed range. The large bleed window caused by rotation of the compression ramp appears near the throat at low Mach number. Low-pressure airflow near the bleed window neutralises the original high-pressure airflow behind the shock train, which decreases the overall pressure of the downstream region of the internal contraction section. To match the lower pressure, the structure of the shock train changes from strong $\lambda$-type to weak $\lambda$-type, and finally to a normal shock wave as backpressure increases at Mach number 2.5. Herein, the total pressure recovery coefficient of the inlet near the critical condition improves by 8.5% as the backpressure ratio (Pe/P0) adds from 13 to 14.6 at Mach number 2.5. It proves that the scheme is effective on terminal shock wave control and inlet performance improvement. In addition, due to the background wave and the bleed window, two kinds of shock wave oscillation occur when the backpressure ratio is 13.1.

Keywords

two-dimensional variable inletlarge bleed windowterminal shock wavenumerical simulationwind tunnel experiment
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1297 , March 2022 , pp. 425 - 449
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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