Compressible flow structures interaction with a two-dimensional ejector: a cold-flow study

Zare-Behtash, H. and Kontis, K. (2009) Compressible flow structures interaction with a two-dimensional ejector: a cold-flow study. Journal of Propulsion and Power, 25(3), pp. 707-716. (doi: 10.2514/1.39315)

[img]
Preview
Text
84653.pdf - Accepted Version

901kB

Abstract

An experimental study has been conducted to examine the interaction of compressible flow structures such as shocks and vortices with a two-dimensional ejector geometry using a shock-tube facility. Three diaphragm pressure ratios ofP4 =P1 = 4, 8, and 12 have been employed, whereP4 is the driver gas pressure andP1 is the pressure within the driven compartment of the shock tube. These lead to incident shock Mach numbers of Ms = 1:34, 1.54, and 1.66, respectively. The length of the driver section of the shock tube was 700 mm. Air was used for both the driver and driven gases. High-speed shadowgraphy was employed to visualize the induced flowfield. Pressure measurements were taken at different locations along the test section to study theflow quantitatively. The induced flow is unsteady and dependent on the degree of compressibility of the initial shock wave generated by the rupture of the diaphragm.

Item Type:Articles
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:Zare-Behtash, Dr Hossein
Authors: Zare-Behtash, H., and Kontis, K.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Journal of Propulsion and Power
Publisher:AIAA
ISSN:0748-4658
ISSN (Online):1533-3876
Copyright Holders:Copyright © 2009 American Institute of Aeronautics and Astronautics
First Published:First published in Journal of Propulsion and Power 25(3):707-716
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher.

University Staff: Request a correction | Enlighten Editors: Update this record