Hypersonic Laminar Boundary Layer Transition on 8 Foot Long 10 Degrees Cone PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Hypersonic Laminar Boundary Layer Transition on 8 Foot Long 10 Degrees Cone PDF full book. Access full book title Hypersonic Laminar Boundary Layer Transition on 8 Foot Long 10 Degrees Cone by H. T. Nagamatsu. Download full books in PDF and EPUB format.
Author: H. T. Nagamatsu
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
Get Book Here
Book Description
Author: H. T. Nagamatsu
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
Get Book Here
Book Description
Author: Henry T. Nagamatsu
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 46
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 760
Get Book Here
Book Description
Author: Michael C. Fischer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 76
Get Book Here
Book Description
Boundary layer transition on nose cones at hypersonic speeds.
Author: Kenneth F. Stetson
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 116
Get Book Here
Book Description
This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
Author: N. B. Wood
Publisher:
ISBN:
Category :
Languages : en
Pages : 41
Get Book Here
Book Description
Author: Kenneth F. Stetson
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 92
Get Book Here
Book Description
Author: E. R. Van Driest
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 108
Get Book Here
Book Description
Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Author: H. T. Nagamatsu
Publisher:
ISBN:
Category :
Languages : en
Pages : 55
Get Book Here
Book Description
An investigation was conducted in a hypersonic shock tunnel to study the laminar boundary layer transition on a highly cooled 10-degree cone of 4-foot length over the Mach number range of 8.5 to 10.5 with a stagnation temperature of 1400K. The effects on transition of tip surface roughness, tip bluntness, and =2-degree angle of attack were investigated. With fast response thin film surface heat transfer gauges, it was possible to detect the passage of turbulent bursts that appeared at the beginning of transition. It was found that the surface roughness greatly promoted transition in the proper Reynolds number range. The Reynolds number for the beginning and end of transition at the 8.5 Mach number location were 3,800,000 to 9,600,000 and 2,200,000 to 4,200,000 for the smooth sharp tip and rough sharp tip, respectively. The local skin friction data agreed with the heat transfer data through Reynolds analogy. The tip bluntness data showed a strong delay in the beginning of transition for a cone base to tip diameter ratio of 20, approximately a 35% increase in Reynolds number over that of the smooth sharp tip case. The angle of attack data indicated the cross flow to have a strong influence on transition by promoting it on the sheltered side of the cone and delaying it on the windward side. (Author).
Author: V. DiCristina
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 8
Get Book Here
Book Description
