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Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model

Wepler, U. and Koschel, W. (2002) Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model. In: AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, pp. 1-10. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, IN, 7 - 10 July 2002.

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Abstract

For the design of airbreathing hypersonic vehicles the simulation of the flow inside the propulsion system is of essential interest. Due to the importance of supersonic combustion in airbreathing hypersonic propulsion the flowfield within a scramjet combustor model has been investigated numerically. In the model hydrogen was injected through a symmetric wedge parallel into a heated Mach 2.0 air stream. The simulated test conditions correspond to a free flight Mach number up to Ma=5.5.

Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2002, monograph_id=AIAA 2002-3572,
Title:Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model
Authors:
AuthorsInstitution or Email of Authors
Wepler, U.UNSPECIFIED
Koschel, W.UNSPECIFIED
Date:2002
Journal or Publication Title:AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Page Range:pp. 1-10
Editors:
EditorsEmail
American Institute of Aeronautics and Astronautics, UNSPECIFIED
Status:Published
Event Title:38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, IN, 7 - 10 July 2002
Organizer:American Institute of Aeronautics and Astronautics
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):E -- no assignement
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion
Deposited By: Monika Lohmiller
Deposited On:16 Sep 2005
Last Modified:06 Jan 2010 13:58

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