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A numerical study on the effect of the flow control using bleeding systems in a bump-type inlet

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Abstract

In many supersonic inlets, several oblique shock waves are followed by a terminal normal shock wave. The normal shock-wave/turbulent boundary-layer interaction is critical with respect to its influence on the development of boundary layer throughout the subsonic diffuser and the total pressure recovery at the engine face. In the current study, the bump-type inlet was designed for two oblique shock waves and a normal shock wave. In addition, a porous surface was installed underneath the root of the normal shock wave. The effect of flow control on the interaction between the normal shock wave and turbulent boundary layer in supersonic inlets by using the bleeding system was investigated numerically and was evaluated with respect to the inlet performance parameters.

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Authors and Affiliations

  1. Department of Aircraft Maintenance, Chodang University, Muan, 534-701, Korea

    Sang Dug Kim

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  1. Sang Dug Kim
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Correspondence to Sang Dug Kim.

Additional information

Recommended by Associate Editor Jungil Lee

Sangdug Kim is a Professor at the Department of Aircraft maintenance, Chodang University. Prior to joining the faculty at Chodang University, he was a Senior Researcher at UNISON. He earned his Ph.D. from Yeungnam University in 2000. Dr. Kim’s research interests are in the area of CFD, applied aerodynamics, and multiphase flows.

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Kim, S.D. A numerical study on the effect of the flow control using bleeding systems in a bump-type inlet. J Mech Sci Technol 31, 5821–5828 (2017). https://doi.org/10.1007/s12206-017-1124-y

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  • DOI: https://doi.org/10.1007/s12206-017-1124-y

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