Author: Don W. Jillie
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate
Author: Don W. Jillie
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate/ by Don W. Jillie; Edward J. Hopkins
Author: Don W. Jillie
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Effects of Mach Number, Leading-edge Bluntness, and Sweep on Boundary-layer Transition on a Flat Plate
Author: DON W. JILLIE
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The effects of leading-edge bluntness and sweep on boundary-layer transition on flat plate models were investigated at Mach numbers of 2.00, 2.50, 3.00, and 4.00. The effect of sweep on transition was also determined on a flat plate model equipped with an elliptical nose at a Mach number of 0.27. Models used for the supersonic investigation had leading-edge radii varying from 0.0005 to 0.040 inch. The free-stream unit Reynolds number was held constant at 15 million per foot for the supersonic tests and the angle of attack was 0 degrees. Surface flow conditions were determined by visual observation and recorded photographically. For the models with the blunter leading edges, the transition Reynolds number (based on free-stream flow conditions) was approximately doubled by an increase in Mach number from 2.50 to 4.00; and nearly the same result was predicted from shock-loss considerations. At all supersonic Mach numbers, increases in sweep reduced the transition Reynolds number and the amount of reduction increased with increases in bluntness. The shock-loss method considerably underestimated the sweep effects, with swept wings. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The effects of leading-edge bluntness and sweep on boundary-layer transition on flat plate models were investigated at Mach numbers of 2.00, 2.50, 3.00, and 4.00. The effect of sweep on transition was also determined on a flat plate model equipped with an elliptical nose at a Mach number of 0.27. Models used for the supersonic investigation had leading-edge radii varying from 0.0005 to 0.040 inch. The free-stream unit Reynolds number was held constant at 15 million per foot for the supersonic tests and the angle of attack was 0 degrees. Surface flow conditions were determined by visual observation and recorded photographically. For the models with the blunter leading edges, the transition Reynolds number (based on free-stream flow conditions) was approximately doubled by an increase in Mach number from 2.50 to 4.00; and nearly the same result was predicted from shock-loss considerations. At all supersonic Mach numbers, increases in sweep reduced the transition Reynolds number and the amount of reduction increased with increases in bluntness. The shock-loss method considerably underestimated the sweep effects, with swept wings. (Author).
Effect of Mach Number, Leading-edge Bluntnes, and Sweep on Boundary-layer Transition on a Flat Plate
Author: Don W. Jillie
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Charts for Estimating Boundary-layer Transition on Flat Plates
Author: Edward J. Hopkins
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36
Book Description
Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds
Author: Gary T. Chapman
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
Book Description
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 260
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 260
Book Description
Hypersonic Aerodynamic Characteristics of Two Delta-wing X-15 Airplane Configurations
Author: Theodore J. Goldberg
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Book Description
Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
Book Description
Hypersonic aerodynamic characteristics of delta wing x- 15 airplane configurations.
Considerations Regarding the Evaluation and Reduction of Supersonic Skin Friction
Author: John B. Peterson
Publisher:
ISBN:
Category : Skin friction (Aerodynamics)
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Skin friction (Aerodynamics)
Languages : en
Pages : 28
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 356
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 356
Book Description