Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 21
Book Description
The results indicate that the trend found previously of an increase in boundary-layer transition Reynolds number with increase in model cooling continued to higher Reynolds numbers. The highest transition Reynolds number obtained with cooling was 28,500,000. At this Reynolds number, the classical Tollmien-Schlichting wave type of boundary-layer number, the instability was apparently overshadowed by surface roughness effects. The results indicated that, when transition was fixed by surface irregularities or airstream flow disturbances, cooling was not effective in obtaining laminar flow behind the irregularity or disturbances.
An Extension of the Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 21
Book Description
The results indicate that the trend found previously of an increase in boundary-layer transition Reynolds number with increase in model cooling continued to higher Reynolds numbers. The highest transition Reynolds number obtained with cooling was 28,500,000. At this Reynolds number, the classical Tollmien-Schlichting wave type of boundary-layer number, the instability was apparently overshadowed by surface roughness effects. The results indicated that, when transition was fixed by surface irregularities or airstream flow disturbances, cooling was not effective in obtaining laminar flow behind the irregularity or disturbances.
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 21
Book Description
The results indicate that the trend found previously of an increase in boundary-layer transition Reynolds number with increase in model cooling continued to higher Reynolds numbers. The highest transition Reynolds number obtained with cooling was 28,500,000. At this Reynolds number, the classical Tollmien-Schlichting wave type of boundary-layer number, the instability was apparently overshadowed by surface roughness effects. The results indicated that, when transition was fixed by surface irregularities or airstream flow disturbances, cooling was not effective in obtaining laminar flow behind the irregularity or disturbances.
Journal of the Royal Aeronautical Society
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 976
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 976
Book Description
The Journal of the Royal Aeronautical Society
Author: Royal Aeronautical Society
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 938
Book Description
Handbook of Supersonic Aerodynamics
Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 608
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 608
Book Description
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
Book Description
The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106
Author: Morton Cooper
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 42
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 42
Book Description
The Influence of Low Wall Temperature on Boundary-Layer Transition and Local Heat Transfer on 2-Inch-Diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 10(exp 6)
Author: Morton Cooper
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88
Author: Benjamine J. Garland
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
Book Description
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 136
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 136
Book Description