Analysis of unsteady pressure measurements in the unstart of a Mach 6.58 hypersonic intake

Venkataraman, NS and Rao, SMV (2023) Analysis of unsteady pressure measurements in the unstart of a Mach 6.58 hypersonic intake. In: 25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2023, 28 May 2023through 1 June 2023, Bengaluru.

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Abstract

An Scramjet intake, with two external and two internal ramps, was tested at freestream Mach number of 6.58 in Ludweig mode on Hypersonic Shock Tunnel (HST-2) at IISc. Unstart was induced using a wedge-based flap at the isolator exit. A bypass flowpath with a rampside bleed was designed to duct the excess mass build up in the isolator during high throttle ratio operation. While the modified intake did not restart, it exhibited a suppression of large-amplitude oscillations and no subsonic spillage was seen in Schlieren images. Further corroboration with pressure measurements will help in analysing this case © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2023
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to American Institute of Aeronautics and Astronautics Inc, AIAA.
Keywords:	Flow path; Freestream mach number; Hypersonic intake; Large amplitude oscillation; Schlieren image; Shock tunnel; Subsonics; Unstart; Unsteady pressure measurements, Pressure measurement
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	20 Dec 2024 09:51
Last Modified:	20 Dec 2024 09:51
URI:	http://eprints.iisc.ac.in/id/eprint/85944

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