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Active Control of the Compressible Boundary Layer on an Infinite Supersonic Swept Wing with a Supersonic Leading Edge by Suction and Cooling

Brouard, E. (1996) Active Control of the Compressible Boundary Layer on an Infinite Supersonic Swept Wing with a Supersonic Leading Edge by Suction and Cooling. DLR-Interner Bericht. 129-96/17, 49 S.

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Abstract

A study of the laminar/turbulent transition have been conducted at the Institute of Design Aerodynamics (DLR Braunschweig) in order to investigate new supersonic configurations. By means of boundary- layer computations and transition predictions based on the linear stability theory, the potential of different boundary-layer control methods has been shown for delaying the transition over a infinite supersonic swept wing with a supersonic leading edge. The methods presented in this paper to delay the transition are suction and wall cooling. As far as laminarization is concerned, both seem to have great potential.

Document Type:Monograph (DLR-Interner Bericht)
Additional Information: LIDO-Berichtsjahr=1996,
Title:Active Control of the Compressible Boundary Layer on an Infinite Supersonic Swept Wing with a Supersonic Leading Edge by Suction and Cooling
Authors:
AuthorsInstitution or Email of Authors
Brouard, E.UNSPECIFIED
Date:1996
Number of Pages:49
Status:Published
Keywords:Transition, compressible boundary layer, laminarization, suction wall cooling
HGF - Research field:UNSPECIFIED
HGF - Program:Aeronautics
HGF - Program Themes:other
DLR - Research area:UNSPECIFIED
DLR - Program:L DT - Drehflüglertechnologien
DLR - Research theme (Project):W - Zukünftige Raumtransporter - Entwurf und Simulationsmethoden für Raumtransporter (old)
Location: Köln-Porz , Braunschweig , Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Institut für Entwurfsaerodynamik
Deposited By: elib DLR-Beauftragter
Deposited On:03 Apr 2006
Last Modified:27 Apr 2009 10:06

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