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Influence of Off-body Energy Addition on an Oblique Shock Wave in a Supersonic Flow

Zaidi, S.H. and Beck, Walter and Howard, P.J. and Shneider, M.N. and Macheret, S.O. and Miles, R.B. (2005) Influence of Off-body Energy Addition on an Oblique Shock Wave in a Supersonic Flow. 21st International Congress on Instrumentation in Aerospace Simulation Facilities, 2005-08-29 - 2005-09-01, Sendai International Center, Sendai, JAPAN. ISBN 0-7803-9097-0.

Full text not available from this repository.

Abstract

It has been proposed that one way of reducing the sonic boom is to deposit energy upstream of the vehicle. A computational and experimental study has been carried out on the near-field flow around a wedge model placed in a Mach 2.4 wind tunnel, where a Nd:YAG laser beam is used to breakdown the air upstream of the wedge, leading to a hot spot of gas which interacts with the wedge oblique shock. These interactions are studied with the help of time-resolved Schlieren (using a MHz rate camera) and using four sequentially placed pressure sensors, located in the region of impingement of the oblique shock on the floor; here they measure the effect of the energy deposition on the shockinduced pressures on the floor. 2D Euler calculations are compared with the wind tunnel results. Both numerical and experimental results agree quite well in the relative pressure levels before and after the shock impingement position, and also in the qualitative behavior of the pressure levels as a function of time after the discharge. The presence of other extraneous shocks and also the well-developed, large, turbulent boundary layer on the tunnel floor hindered a further quantitative comparison of experimental and computational results.

Document Type:Conference or Workshop Item (Speech, Paper)
Additional Information:Dr. Beck war zum Zeitpunkt der Tagung in den USA
Title:Influence of Off-body Energy Addition on an Oblique Shock Wave in a Supersonic Flow
Authors:
AuthorsInstitution or Email of Authors
Zaidi, S.H.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USA
Beck, WalterUNSPECIFIED
Howard, P.J.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USA
Shneider, M.N.Department of Mechanical and Aerospace EngineeringPrinceton University, Princeton NJ 08540, USA,
Macheret, S.O.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USA
Miles, R.B.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USA
Date:2005
Refereed publication:No
In SCOPUS:No
In ISI Web of Science:No
Volume:CD-ROM
Page Range:pp. 83-89
Editors:
EditorsEmail
IEEE, UNSPECIFIED
Series Name:Conference Proceedings, Session 5, 5-1
ISBN:0-7803-9097-0
Status:Published
Keywords:time-resolved Schlieren, 2D Euler, turbulent boundary layer
Event Title:21st International Congress on Instrumentation in Aerospace Simulation Facilities
Event Location:Sendai International Center, Sendai, JAPAN
Event Type:international Conference
Event Dates:2005-08-29 - 2005-09-01
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Deposited By: Ilka Micknaus
Deposited On:21 Aug 2007
Last Modified:27 Apr 2009 14:07

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