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Grenzschichtabsaugung in Hyperschall-Einlaeufen.

Schulte, D. (V) and Henckels, A. (1996) Grenzschichtabsaugung in Hyperschall-Einlaeufen. 10. DGLR-Fach-Symposium "Strömungen mit Ablösung", DLR Braunschweig, 11.-13. November 1996 (Proceedings in Vorbereitung)..

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Shock-induced boundary layer separation has an important influence on the efficiency of hypersonic inlet systems. A method to reduce the boundary layer separation is the implementation of boundary layer bleed. Results are presented for the use of a planar bleed slot at a generic flat plate model for laminar boundary layer flow at a Mach number of 6. The wind tunnel models and the wind tunnel test procedure are optimized by using computational fluid dynamics. An analytical method to predict the key parameters of the boundary layer bleed is presented. The possible reduction of the boundary layer separation and of the thermal loads on the walls by using bleed is demonstrated by results of wind tunnel tests and favorable design parameters for bleed slots are determined.

Document Type:Conference or Workshop Item (Speech)
Additional Information: LIDO-Berichtsjahr=1996,
Title:Grenzschichtabsaugung in Hyperschall-Einlaeufen.
AuthorsInstitution or Email of Authors
Keywords:Grenzschichtabsaugung, Hyperschall-Einlauf.
Event Title:10. DGLR-Fach-Symposium "Strömungen mit Ablösung", DLR Braunschweig, 11.-13. November 1996 (Proceedings in Vorbereitung).
HGF - Research field:UNSPECIFIED
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:UNSPECIFIED
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):UNSPECIFIED
Location: Köln-Porz
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: elib DLR-Beauftragter
Deposited On:02 Apr 2006
Last Modified:27 Apr 2009 05:30

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