Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack
Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack

Author: Donald M. Kuehn

Publisher:

Published: 1961

Total Pages: 36

ISBN-13:

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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.

Scientific and Technical Aerospace Reports
Scientific and Technical Aerospace Reports

Author:

Publisher:

Published: 1979

Total Pages: 738

ISBN-13:

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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.

Experimental Study on High Subsonic Turbulent Flow Incipient Separation
Experimental Study on High Subsonic Turbulent Flow Incipient Separation

Author: Jain-Ming Wu

Publisher:

Published: 1976

Total Pages: 68

ISBN-13:

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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.

Shock Wave-Boundary-Layer Interactions
Shock Wave-Boundary-Layer Interactions

Author: Holger Babinsky

Publisher: Cambridge University Press

Published: 2011-09-12

Total Pages: 481

ISBN-13: 1139498649

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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.

Research on Supersonic Turbulent Separated and Reattached Flows
Research on Supersonic Turbulent Separated and Reattached Flows

Author: Seymour M. Bogdonoff

Publisher:

Published: 1975

Total Pages: 94

ISBN-13:

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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.