Preprint Article Version 1 NOT YET PEER-REVIEWED

Design and Numerical Analysis of Mixed Compression Inlet of a Shcramjet Engine

  1. Department of Mechanical Engineering, Institute of Engineering, Tribhuvan University, P.O.Box 8212, Kirtipur, Kathmandu, Nepal
Version 1 : Received: 15 November 2016 / Approved: 16 November 2016 / Online: 16 November 2016 (09:32:59 CET)

How to cite: Acharya, N.; Sharma, S.; Silwal, L.; Bhattrai, S. Design and Numerical Analysis of Mixed Compression Inlet of a Shcramjet Engine. Preprints 2016, 2016110079 (doi: 10.20944/preprints201611.0079.v1). Acharya, N.; Sharma, S.; Silwal, L.; Bhattrai, S. Design and Numerical Analysis of Mixed Compression Inlet of a Shcramjet Engine. Preprints 2016, 2016110079 (doi: 10.20944/preprints201611.0079.v1).

Abstract

The aim of this work is to present a design approach of a Shock-Induced Combustion Ramjet (Shcramjet) inlet, and present its optimization in terms of the flow and geometrical parameters. The flow properties of mixed compression type inlet of a Shcramjet are examined using analytical and numerical techniques. The geometries obtained with variations in the wedge angles, length, height and cowl lip positions are used to study the flow characteristics of inlet, identifying bow shock temperature ratio as the optimization parameter. The two-dimensional geometries of two-shock and three-shock inlet models designed analytically for shock-on-lip condition at Mach 12.5 and an altitude of 32.5 km are numerically simulated in OpenFOAM CFD Toolbox. A density based compressible CFD solver based on central upwind schemes of Kurganov and Tadmore is used to solve 2D inviscid Euler equations. The inlet total pressure recovery is expressed as a function of temperature ratios of compression shocks, and is found to have a maxima at a bow shock temperature ratio at the design condition when the bow and external shocks have equal strengths. The effect of considering the flow to be calorically imperfect is studied numerically, and the deviation from the analytical design is presented.

Subject Areas

oblique detonation wave; mixed compression inlet; inlet diffusion; total pressure recovery

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