Limitations of two-shock mixed compression intakes at hypersonic mach numbers

Vedam, AJ and Devaraj, MKK and Jagadeesh, G (2019) Limitations of two-shock mixed compression intakes at hypersonic mach numbers. In: AIAA Aviation 2019 Forum, 17-21 June 2019, Dallas; United States, pp. 1-11.

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Abstract

The air intake in a hypersonic air-breathing engine is an crucial component of ramjet and scramjet design. The intake primarily consists of a spike or a cone, from which a shock originates and compresses the incoming air to higher pressures, for combustion to take place. The performance of a two-shock mixed compression supersonic and hypersonic intake has been predicted using established analytical models in the present study. This method is applied to a rectangular as well as an axisymmetric intake configuration, with the Kantrowitz Limit as a constraint. The intake has been designed with shock on lip and shock on shoulder conditions, and the same has been verified using CFD. The findings confirm that the compression of a two-shock system is insufficient for practical applications in the hypersonic regime. © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	AIAA Aviation 2019 Forum
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	cited By 0; Conference of AIAA Aviation 2019 Forum ; Conference Date: 17 June 2019 Through 21 June 2019; Conference Code:228939
Keywords:	Aviation; Ramjet engines, Air breathing engines; Axisymmetric; Mixed compressions; Shock system; Shoulder conditions; Supersonic and hypersonic, Hypersonic inlets
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	01 Feb 2021 08:58
Last Modified:	01 Feb 2021 08:58
URI:	http://eprints.iisc.ac.in/id/eprint/67898

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