ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

VISUALIZATION AND ANALYSIS OF ACCELERATING TRANSONIC FLOW OVER TYPICAL LAUNCH VEHICLE MODEL USING IMAGE PROCESSING

Singh, DB and Yanamashetti, G and Suryanarayana, GK and Jagadeesh, G (2024) VISUALIZATION AND ANALYSIS OF ACCELERATING TRANSONIC FLOW OVER TYPICAL LAUNCH VEHICLE MODEL USING IMAGE PROCESSING. In: Journal of Flow Visualization and Image Processing, 31 (4). pp. 55-66.

[img] PDF
Jou_Flo_Vis_Ima_Pro_31_4_ 55_66_2024.pdf - Published Version
Restricted to Registered users only

Download (1MB) | Request a copy
Official URL: https://doi.org/10.1615/JFlowVisImageProc.20240495...

Abstract

The formation and transit of the Lambda-shock system that occurs over the payload region of a launch vehicle at transonic Mach numbers have been captured using high-speed shadowgraphy and unsteady pressure measurements. The test section Mach number (M) was varied from 0.85 to 0.95 continuously. Analyses based on image processing indicate systematic downstream movement of the shock system until M = 0.92 and rapid oscillations upstream and downstream of the mean position at higher M. Unsteady pressure measurements indicate large fluctuations in this range, suggesting localized alternating flow over the payload. Pressure fluctuations obtained during Mach-sweep mode indicate higher values as compared to results at constant Mach number at the same angle of attack (α), suggesting that (dM/dt) is an important parameter that needs to be properly simulated in wind tunnel tests in order to characterize the flight performance of launch vehicles at transonic Mach numbers. © 2024 by Begell House, Inc.

Item Type: Journal Article
Publication: Journal of Flow Visualization and Image Processing
Publisher: Begell House Inc.
Additional Information: The copyright for this article belongs to Begell House Inc.
Keywords: Angle of attack; Image analysis; Launch vehicles; Pressure measurement; Supersonic aircraft; Wind tunnels, Down-stream; Images processing; Pressure fluctuation; Shock system; SWBLI; Transonic buffet; Unsteady pressure fluctuation; Unsteady pressure measurements; Unsteady pressures; � shock system, Mach number
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 05 Jun 2024 05:25
Last Modified: 05 Jun 2024 05:25
URI: https://eprints.iisc.ac.in/id/eprint/85222

Actions (login required)

View Item View Item