Krogmann, P. (1994) Hyperboloid/Flare Experiments at Mach 6.8 in RWG. DLR-Interner Bericht. 223 - 94 C 44, 85 S.
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An experimental investigation on a hyperboloid/flare configuration was performed in the DLR Ludwieg Tube Facility at Goetttingen (RWG) at a Mach number of M oo = 6.8 at various unit Reynolds numbers in the range from Re oo/m = 3.5 x 10 6 to Me oo/m = 15 x 10 6. Aside from pressure and heat transfer distribution measurements along the surface of the model, the extent of the separated flow region in front on the flare and its dependency on Reynolds number was investigated. Surface oil flow visualization, Schlieren observations, and thermal mapping, utilizing thermo- sensitive liquid crystal coating, supplemented and confirmed the pressure and heat transfer measurements. The separated region in front of the flare and its dependency on Reynolds number was investigated. Surface oil flow visualizations, Schlieren observationsand thermal mapping, utilizing thermo-sensitive liquid crystal coating, supplemented and confirmed the pressure and heat transfer measurements. The separated region extended upstream of the hinge line about = 18% to = 25% of the total model length in the Reynolds number range tested.
|Document Type:||Monograph (DLR-Interner Bericht)|
|Title:||Hyperboloid/Flare Experiments at Mach 6.8 in RWG|
|Number of Pages:||85|
|Keywords:||Hypersonic flow, Shock boundary layer interaction, Separation, Flow visualization, Reynolds number, Ludwieg Tube wind tunnel|
|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 , Braunschweig , Göttingen|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > Institut für Strömungsmechanik > Institut für Experimentelle Strömungsmechanik|
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||03 Apr 2006|
|Last Modified:||27 Apr 2009 10:08|
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