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The Pressure Rise Associated With Shock Induced Laminar Boundary Layer Separation
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Book Synopsis The Pressure Rise Associated with Shock-induced Laminar Boundary Layer Separation by : Charles Keith Cretcher
Download or read book The Pressure Rise Associated with Shock-induced Laminar Boundary Layer Separation written by Charles Keith Cretcher and published by . This book was released on 1963 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Rise Associated with Shock-induced Boundary-layer Separation by : Eugene S. Love
Download or read book Pressure Rise Associated with Shock-induced Boundary-layer Separation written by Eugene S. Love and published by . This book was released on 1955 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some recent contributions to the problem of shock-induced separation of the boundary layer are examined, and additional analytical and experimental results are presented. The probable ranges of pressure rises and flow deflections associated with separation are indicated. Consideration is given to the effects of Mach number, adverse pressure gradient, and Reynolds number for laminar boundary layers and to the effects of Mach number, Reynolds number, and ratio of sepcific heats for turbulent boundary layers.
Book Synopsis Some Observations on Maximum Pressure Rise Across Shocks Without Boundary-layer Separation on Airfoils at Transonic Speeds by : Walter F. Lindsey
Download or read book Some Observations on Maximum Pressure Rise Across Shocks Without Boundary-layer Separation on Airfoils at Transonic Speeds written by Walter F. Lindsey and published by . This book was released on 1956 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the two-dimensional flow along flat plates having rounded leading edges has provided additional information on shock-induced separation. The results indicate that laminar boundary layers can sustain the theoretical pressure rise for normal shocks without separating provided that the local Mach numbers are less than about 1.4. The permissible pressure rise across shocks without boundary-layer separation on rounded-leading-edge airfoils having flat sides or convex surfaces was observed to increase with increase in angle of attack and proximity of shock to airfoil leading edge.
Book Synopsis Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers by : Coleman duP. Donaldson
Download or read book Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers written by Coleman duP. Donaldson and published by . This book was released on 1952 with total page 2 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers by : Coleman duP. Donaldson
Download or read book Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers written by Coleman duP. Donaldson and published by . This book was released on 1952 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2,000,000 to 19,000,000. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems.
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 1038 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow by : Michael S. Holden
Download or read book A Study of Flow Separation in Regions of Shock Wave-boundary Layer Interaction in Hypersonic Flow written by Michael S. Holden and published by . This book was released on 1975 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes a theoretical and experimental investigation of the properties of attached and separated regions of shock wave-laminar boundary layer interacting in the strong interaction regime. The flow is studied over a flat plate-wedge compression surface in the high Mach number, low Reynolds number regime where the interaction between the viscous and inviscid regions over the basic flat plate is strong and of fundamental importance to the problem. The theoretical analysis treats the development of the viscous layer and its interaction with the external inviscid stream, using an integral representation for the boundary layer equations. A complementary experimental study investigated the flow over a flat plate-wedge compression surface for a range of free-stream Reynolds number and Mach number conditions in the strong interaction regime.
Download or read book Technical Note written by and published by . This book was released on 1955 with total page 552 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1974 with total page 482 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack by : Donald M. Kuehn
Download or read book Turbulent Boundary-layer Separation Induced by Flares on Cylinders at Zero Angle of Attack written by Donald M. Kuehn and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Report of the National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 872 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Monthly Catalog of United States Government Publications, Cumulative Index by : United States. Superintendent of Documents
Download or read book Monthly Catalog of United States Government Publications, Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1978 with total page 1300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Stresses Around Rectangular Cutouts in Torsion Boxes by : Paul Kuhn
Download or read book Stresses Around Rectangular Cutouts in Torsion Boxes written by Paul Kuhn and published by . This book was released on 1953 with total page 632 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is presented for calculating the stresses produced by rectangular cutouts of any size in torsion boxes. The problem is divided into a "box problem" and a "cover problem." The box problem is a special case of the general method of analyzing torsion boxes without cutouts. In the cover problem, simple shear-lag theory is used to obtain "key" stresses; the final distributions are obtained from these key stresses by means of simple rules or empirical distribution curves. Comparisons with the results from three series of tests in which the dimensions of the cutouts varied over a wide range are shown.
Book Synopsis Attached and Separated Boundary Layers on Highly Cooled, Ablating and Nonablating Models at M by : Donald M. Kuehn
Download or read book Attached and Separated Boundary Layers on Highly Cooled, Ablating and Nonablating Models at M written by Donald M. Kuehn and published by . This book was released on 1967 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Shock Wave-Boundary-Layer Interactions by : Holger Babinsky
Download or read book Shock Wave-Boundary-Layer Interactions written by Holger Babinsky and published by Cambridge University Press. This book was released on 2011-09-12 with total page 481 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Experimental Investigation of Laminar-flow Separation on a Flat Plate Induced by Deflected Trailing-edge Flap at Mach 19 by : Bill Harvey
Download or read book Experimental Investigation of Laminar-flow Separation on a Flat Plate Induced by Deflected Trailing-edge Flap at Mach 19 written by Bill Harvey and published by . This book was released on 1968 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
