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CFD Analysis of radiative heat loading on hypervelocity re-entry vehicles

Karl, Sebastian and Lambert, Markus (2009) CFD Analysis of radiative heat loading on hypervelocity re-entry vehicles. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, 19.-22. Okt. 2009, Bremen.

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Official URL: http://www.aiaa.org

Abstract

Space exploration missions may include atmospheric entries at high velocities (e.g. sample-return, hyperbolic entries) or into an atmosphere with highly radiative constituents (e.g. Jupiter, Titan). The effects of gas radiation in the shock layer can become significant at such flow conditions. This requires adequate modeling of the local absorption and emission properties and the energy transport by radiation. This paper describes a Monte-Carlo based method to solve the radiative transfer equation. The resulting energy sources are coupled to a CFD solver to account for the additional mechanism of radiative energy transport. This approach is validated using a canonical test problem and then applied to the FIRE II flight experiment configuration.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:CFD Analysis of radiative heat loading on hypervelocity re-entry vehicles
Authors:
AuthorsInstitution or Email of Authors
Karl, SebastianSebastian.Karl@dlr.de
Lambert, MarkusMarkus.Lambert@dlr.de
Date:October 2009
Series Name:Online Conference Proceedings
Status:Published
Keywords:Radiation, CFD, re-entry
Event Title:16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Event Location:Bremen
Event Type:international Conference
Event Dates:19.-22. Okt. 2009
Organizer:AIAA, DLR, DGLR
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):W - Grundlagen Raumtransport - numerische Verfahren (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Institute of Aerodynamics and Flow Technology > CASE
Deposited By: Sebastian Karl
Deposited On:25 Nov 2009 10:00
Last Modified:26 Nov 2009 15:03

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