Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 PDF Download

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Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8

Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 PDF Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82

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Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8

Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 PDF Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 82

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Book Description

Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-Layer Transition on Axisymmetric Bodies in Supersonic Flow

Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-Layer Transition on Axisymmetric Bodies in Supersonic Flow PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Book Description
A series of tests has been conducted at free-stream Mach numbers four and eight to determine the effectiveness of three-dimensional boundary-layer trips in promoting transition on very blunt axisymmetric bodies with near equilibrium wall temperatures. Temperature distributions obtained with temperature sensing gages inserted in the model surface were used to locate boundary-layer transition at Mach number four, and qualitative results, based on pitot pressure measurements, were obtained at Mach number eight. A simple modification of a technique proposed by van Driest and Blummer for determining an effective trip size for blunt bodies is shown to yield a correlation applicable to their data on a sphere at Mach number two and the present configurations at Mach number four.

Effect of Centerbody Boundary-layer Removal Near the Throat of Three Conical Nose Inlets at Mach 1.6 to 2.0

Effect of Centerbody Boundary-layer Removal Near the Throat of Three Conical Nose Inlets at Mach 1.6 to 2.0 PDF Author: Emil J. Kremzier
Publisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 22

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Effect of Unsymmetrical Nose-bluntness of the Pressure Distribution Over a 10° Cone at Mach-14

Effect of Unsymmetrical Nose-bluntness of the Pressure Distribution Over a 10° Cone at Mach-14 PDF Author: Otto Walchner
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 35

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Effect of Nose Bluntness on Transition for a Cone and a Hollow Cylinder at Mach Numbers 1.41 and 2.01

Effect of Nose Bluntness on Transition for a Cone and a Hollow Cylinder at Mach Numbers 1.41 and 2.01 PDF Author: William J. Monta
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38

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Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8

Effect of Unit Reynolds Number, Nose Bluntness, Angle of Attack, and Roughness on Transition on a 5° Half-angle Cone at Mach 8 PDF Author: P. Calvin Stainback
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0

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Book Description

Effect of Body Nose Blunting, Control Planform Area, and Leading-edge Bluntness on Aerodynamic Control of a 5 Degree Semivertex Cone at Mach Number 6.9

Effect of Body Nose Blunting, Control Planform Area, and Leading-edge Bluntness on Aerodynamic Control of a 5 Degree Semivertex Cone at Mach Number 6.9 PDF Author: Jim A. Penland
Publisher:
ISBN:
Category :
Languages : en
Pages : 66

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Aerodynamic Interference Effects Caused by Parallel-staged Simple Aerodynamic Configurations at Mach Numbers of 3 and 6

Aerodynamic Interference Effects Caused by Parallel-staged Simple Aerodynamic Configurations at Mach Numbers of 3 and 6 PDF Author: John P. Decker
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 92

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Book Description
Aerodynamic characteristics effected by parallel- staged simple aerodynamic configurations at Mach numbers of 3 and 6.

Effects of Nose Bluntness on Aerodynamic Characteristics of Cruciform-finned Missle Configuration at Mach 1.550 to 2.86

Effects of Nose Bluntness on Aerodynamic Characteristics of Cruciform-finned Missle Configuration at Mach 1.550 to 2.86 PDF Author: Lloyd S. Jernell
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0

Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0 PDF Author: Richard I. Sears
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 22

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Book Description