elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Contact | Deutsch
Fontsize: [-] Text [+]

About the Heat Flux and Skin Friction Prediction of the DLR TAU-code for Turbulent Supersonic Flows

Kovar, Anke and Schülein, Erich and Hannemann, Volker and Karl, Sebastian (2007) About the Heat Flux and Skin Friction Prediction of the DLR TAU-code for Turbulent Supersonic Flows. ODAS 2007 8th ONERA-DLR Aerospace Symposium, 2007-10-17 - 2007-10-19, Göttingen, Germany. (Unpublished)

[img] PDF - Registered users only - Requires a PDF viewer such as GSview, Xpdf or Adobe Acrobat Reader
13kB

Abstract

Surface temperatures of missile configuration at supersonic speeds can easily reach values of 2,000 K depending on Mach number and altitude. Hence, the correct prediction of heat loads is crucial for the choice of materials within the design process of a missile configuration. For many Navier-Stokes-flow solvers it is still a challenging task to correctly predict heat flux and skin friction in turbulent supersonic boundary layers. In the hypersonic regime the flow is laminar in many cases, simplifying the equations and the calculation. In the supersonic speed range the flow along the body is nearly always transitional. The applied turbulence model can have a large influence on the predicted heat load distribution especially in the vicinity of reattachment and divergence zones of the flow. The more complex the flow gets, e.g. due to side-jet-injection, high angles of attack, and the associated flow separation, the more difficult it becomes to predict the heat flux correctly. This is the motivation to assess the heat flux obtained by the TAU-code (Gerhold and Evans, 1999 and Schwamborn et al, 1999), which is an internal development of the German Aerospace Centre (DLR), using an appropriate bench mark experiment which was carried out at DLR. The experiment (Schülein et al, 1996) was performed already a few years ago in the DLR Ludwieg Tube (RWG) at M=5.0 on a flat plate with a transitional boundary layer. It was set up as a 2-dimensional test case in which a shock generator was employed in a way that a shock impinged on the flat plate under different angles. The experiment provides for comparison data including boundary layer velocity profiles, heat flux, skin friction, and surface pressure in the region influenced by the shock and also along the turbulent region upstream of the interaction. First steps of the investigation cover the influence of grid cell resolution as well as the cell stretching within the boundary layer, and the influence of different turbulence models.

Document Type:Conference or Workshop Item (Speech)
Title:About the Heat Flux and Skin Friction Prediction of the DLR TAU-code for Turbulent Supersonic Flows
Authors:
AuthorsInstitution or Email of Authors
Kovar, AnkeUNSPECIFIED
Schülein, ErichUNSPECIFIED
Hannemann, VolkerUNSPECIFIED
Karl, SebastianUNSPECIFIED
Date:15 March 2007
Status:Unpublished
Keywords:Assessment of heat flux, skin friction, DLR-TAU-code, supersonic flows
Event Title:ODAS 2007 8th ONERA-DLR Aerospace Symposium
Event Location:Göttingen, Germany
Event Type:international Conference
Event Dates:2007-10-17 - 2007-10-19
Organizer:DLR Göttingen
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Institute of Aerodynamics and Flow Technology > High Speed Configurations
Deposited By: Dr.rer.nat. Anke Kovar
Deposited On:25 Jun 2007
Last Modified:12 Dec 2013 20:24

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.