Numerical Investigation of the Hypersonic Inlet under Throttling with Heat Source

Nurfathin Zahrolayali; Mohd Rashdan Saad; Azam Che Idris; Mohd Rosdzimin Abdul Rahman

doi:10.37934/cfdl.14.10.7986

Authors

Nurfathin Zahrolayali Department of Mechanical Engineering, Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, Kem Sg. Besi, Kuala Lumpur, Malaysia
Mohd Rashdan Saad Department of Mechanical Engineering, Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, Kem Sg. Besi, Kuala Lumpur, Malaysia
Azam Che Idris Faculty of Integrated Technologies, Universiti Brunei Darussalam, Brunei
Mohd Rosdzimin Abdul Rahman Department of Mechanical Engineering, Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, Kem Sg. Besi, Kuala Lumpur, Malaysia

DOI:

https://doi.org/10.37934/cfdl.14.10.7986

Keywords:

Numerical Simulation, Hypersonic, Shock Wave Boundary Layer, Heat Source, Active Flow Control

Abstract

The influence of using a heat source to manage the shock wave boundary layer interactions (SWBLI) at the hypersonic inlet under throttling were studied numerically. This hypersonic inlet was created for a fluid flow Mach number of 5. The throttling was induced by a plug placed near the intake isolator's outlet. The study's parameters included the heat source power and size. The intake performance indicators were the total pressure recovery and the flow distortion. The position of the heat source was determined by studying the interplay of the shock waves from the compression ramp. The results demonstrated the existence of the shock waves at the heat source, and its influences on the SWBLI inside the isolator. This behaviour, led to an increase in the total pressure recovery and reduction of the flow distortion.

Author Biography

Mohd Rosdzimin Abdul Rahman, Department of Mechanical Engineering, Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, Kem Sg. Besi, Kuala Lumpur, Malaysia

rosdzimin@gmail.com

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