Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators-Reference-Cited by-同舟云学术

Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators

Published:2024-05-03 Issue: Volume: Page:
ISSN:0334-0082
Container-title:International Journal of Turbo & Jet-Engines
language:en
Short-container-title:

Author:

Raj Ritul¹,Joshi Ganapati N.¹,Chandel Sunil²,Mishra Ranjan Kumar³

Affiliation:

1. Department of Aerospace Engineering , 93049 Defence Institute of Advanced Technology , Pune , India

2. Department of Mechanical Engineering , 93049 Defence Institute of Advanced Technology , Pune , India

3. MVJ College of Engineering , Bengaluru , India

Abstract

Abstract A computational study of a three ramped dual duct Rocket Based Combined Cycle (RBCC) engine inlet at scramjet mode using different types of MVG (micro vortex generator) arrays were conducted. The definite geometry of engine inlet was operated at hypersonic speeds of Mach 5 and 7 to study the effect of the arrays of delta ramp (DR), rectangular vane (RRV) and ramp vane (RV) on the pressure recovery, exit Mach number, the mass flow rate and Shock wave Boundary Layer interaction (SWBLI). The study was performed considering same heights for all the configurations of MVG array and were positioned at the point of shock impingement on the ramp which caused the separation bubble. The computational analysis was done using k-omega model in Fluent Workbench of Ansys.

Publisher

Walter de Gruyter GmbH

Link

https://www.degruyter.com/document/doi/10.1515/tjj-2024-0015/pdf

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