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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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|
|Journal or Publication Title:||AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit|
|Page Range:||pp. 1-10|
|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|
|HGF - Program:||Space|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||Space|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||E -- no assignement|
|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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