Laminar Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack PDF Download
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Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 28
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Book Description
Laminar boundary-layer separation induced by a flare on a cylindrical body of revolution has been experimentally investigated in the Mach number range of 2.0 to 5.5. The Reynolds number range (based on boundary-layer thickness) was 1x103 to 30x103. Geometric variables were nose shape, cylinder length, and flare angle. Test variables were Mach number, Reynolds number, and heat transfer. The purpose of the investigation was to determine which of these variables most influence laminar boundary-layer separation on a cylinder-flare configuration and to provide data that will aid in the prediction of laminar separation.
Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 28
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Book Description
Laminar boundary-layer separation induced by a flare on a cylindrical body of revolution has been experimentally investigated in the Mach number range of 2.0 to 5.5. The Reynolds number range (based on boundary-layer thickness) was 1x103 to 30x103. Geometric variables were nose shape, cylinder length, and flare angle. Test variables were Mach number, Reynolds number, and heat transfer. The purpose of the investigation was to determine which of these variables most influence laminar boundary-layer separation on a cylinder-flare configuration and to provide data that will aid in the prediction of laminar separation.
Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 38
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Book Description
Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 36
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Book Description
Separation caused by the pressure rise induced by flares has been experimentally investigated in the Mach number range of 1.5 to 5.0 and in the Reynolds number range (based on boundary-layer thickness) of 1.5X104 to 12X104. The purpose of the investigation was to determine the model geometry and flow conditions for which separation can be expected for a turbulent boundary layer of zero pressure gradient on the cylinder approaching the flare. Comparisons are made of the boundary-layer-separation characteristics of these three-dimensional flares with two-dimensional separation results from a previous investigation.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 522
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Book Description
Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 32
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Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 492
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 796
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 168
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Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 364
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Author: R. E. Wilson
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 364
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