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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

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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.

Item URL in elib:https://elib.dlr.de/50206/
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 AuthorsAuthors ORCID iD
Zaidi, S.H.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USAUNSPECIFIED
Beck, WalterUNSPECIFIEDUNSPECIFIED
Howard, P.J.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USAUNSPECIFIED
Shneider, M.N.Department of Mechanical and Aerospace EngineeringPrinceton University, Princeton NJ 08540, USA,UNSPECIFIED
Macheret, S.O.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USAUNSPECIFIED
Miles, R.B.Department of Mechanical and Aerospace Engineering, Princeton University, Princeton NJ 08540, USAUNSPECIFIED
Date:2005
Refereed publication:No
Open Access:No
Gold Open Access: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 (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Deposited By: Micknaus, Ilka
Deposited On:21 Aug 2007
Last Modified:27 Apr 2009 14:07

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