The prediction of free separation of a supersonic turbulent boundary layer including effects of upstream flow history PDF Download
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Author: Donald Albert Hall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 124
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Book Description
Author: Donald Albert Hall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 124
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Book Description
Author:
Publisher:
ISBN:
Category : Chemistry
Languages : en
Pages : 544
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Author: Seymour M. Bogdonoff
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 94
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Book Description
Basic research programs are reported with fundamental applications to supersonic flight. The experimental studies made use of the unique capabilities of the high Reynolds number Mach 3 facility. The experimental programs concentrated on phenomena associated with incipient separation and separation of turbulent boundary layers over a large Reynolds number range. The reattachment phenomena of a shear layer was also studied in great depth.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 790
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Author: Rasol Namnabat
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 222
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Book Description
Author: Alexander J. Smits
Publisher: A I P Press
ISBN:
Category : Science
Languages : en
Pages : 384
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Book Description
Using the most recent data, this text describes the physical mechanisms of turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows. DLC: Aerodynamics, Supersonic.
Author: P. H. Oosthuizen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 41
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Book Description
A theoretical study of the effects of the wall boundary layer on the supersonic flow around a sharp convex corner is presented. Fundamentally different methods of analysis are adopted for laminar and for turbulent boundary layers. In the case of interactions involving laminar boundary layers, an analysis based on the use of classical boundary layer theory is used. Results of numerical calculations carried out using this analysis to predict the effects of the major governing parameters are presented. In all cases, a considerable upstream and downstream influence is predicted. A simplified form of this analysis, closely related to that of Curle, is also presented, this analysis leading to a simple set of explicit equations describing the flow quantities in the interaction region. Comparison of the simplified analysis with results obtained from the full analysis indicated, as is to be expected, that the simplified analysis will only give acceptable results for small expansion angles and moderate Mach numbers. In the case of turbulent boundary layer interactions, an analysis based on the assumption that there is no upstream influence and that the major portion of the expansion occurs in an effectively inviscid manner is adopted, the flow properties being calculated by the method of rotational characteristics. (Author).
Author: E. R. Van Driest
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 108
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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: Earl A. Price (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 82
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Book Description
