Incipient Separation of a Turbulent Boundary Layer at High Reynolds Number in Two- Dimensional Supersonic Flow Over a Compression Corner PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Book Description
Author: C. Herbert Law
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 120
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Book Description
Author: Jain-Ming Wu
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 68
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Book Description
For flow over a two-dimensional ramp compression corner case, an experimental investigation to determine the incipient separation was carried out at Mach numbers between 0.55 and 0.9 and Reynolds numbers (based on undisturbed boundary layer thickness) between 350,000 and 690,000. Detailed surface pressure, pitot traversing and oil flow data were obtained for each ramp angle case. Two-dimensionality of the ramp compression corners was verified by the surface oil flow. A major finding of this study is that the incipient separation ramp angle is relatively independent of Mach number and Reynolds number within the range studied. The incipient separation ramp angle was found to be about 22.5 degrees.
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: Donald M. Kuehn
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 36
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Book Description
Separation caused by the pressure rise induced by flares has been experimentally investigated in the Mach number range of 1.5 to 5.0 and in the Reynolds number range (based on boundary-layer thickness) of 1.5X104 to 12X104. The purpose of the investigation was to determine the model geometry and flow conditions for which separation can be expected for a turbulent boundary layer of zero pressure gradient on the cylinder approaching the flare. Comparisons are made of the boundary-layer-separation characteristics of these three-dimensional flares with two-dimensional separation results from a previous investigation.
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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Book Description
Author: E. T. Curran
Publisher: AIAA
ISBN: 9781600864414
Category : Airplanes
Languages : en
Pages : 1354
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 738
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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: Victor V. Kozlov
Publisher: Springer Science & Business Media
ISBN: 3642844472
Category : Science
Languages : en
Pages : 907
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Book Description
Separated flows and jets are closely linked in a variety of applications. They are of great importance in various fields of fluid mechanics including vehicle efficiency, technical branches concerned with gas/liquid flows, atmospheric effects on various constructions, etc. Knowledge of the physics of separated flows and jets and the development of reliable control techniques are prerequisite for future progress in the field. These aspects were in focus during the IUTAM-Symposium which was held in Novosibirsk, 9-13 July, 1990. This volume contains a selection of papers presenting recent results of theoretical and numerical studies as well as experimental work on separated flows and jets. The topics include sub- and supersonic, laminar and turbulent separation as well as organized structures in separated flows and jets. The reader will find here the state of the art and major trends for research in this field of aero-hydrodynamics.
Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
