Interaction Between Shock Waves And Turbulent Or Transitional Boundary Layers At Mach Number 3 PDF Download
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| Author | : Edelbert E Irish |
| Publisher | : Hassell Street Press |
| Total Pages | : 160 |
| Release | : 2021-09-09 |
| Genre | : |
| ISBN | : 9781014788016 |
Download Interaction Between Shock Waves and Turbulent Or Transitional Boundary Layers at Mach Number 3. Book in PDF, ePub and Kindle
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
| Author | : Edelbert Eugene Irish |
| Publisher | : |
| Total Pages | : 160 |
| Release | : 1957 |
| Genre | : Aeronautics |
| ISBN | : |
Download Interaction Between Shock Waves and Turbulent Or Transitional Boundary Layers at Mach Number 3 Book in PDF, ePub and Kindle
| Author | : C. Herbert Law |
| Publisher | : |
| Total Pages | : 52 |
| Release | : 1975 |
| Genre | : Aerodynamic heating |
| ISBN | : |
Download Three-dimensional Shock Wave-turbulent Boundary Layer Interactions at Mach 6 Book in PDF, ePub and Kindle
Experimental results of an investigation of the three-dimensional interaction between a skewed shock wave and a turbulent boundary layer are presented. Surface pressure and heat transfer distributions and oil flow photographs were obtained at a freestream Mach number of 5.85 and two Reynolds numbers of ten and twenty million per foot. The model configuration consisted of a shock generator mounted perpendicularly to a flat plate. The shock generator leading edge was sharp and nonswept and intersected the flat plate surface about 8.5 inches downstream of the flat plate leading edge. The shock generator surface was 7.55 inches long and 3 inches high and its angle to the freestream flow was adjusted from 4 to 20 degrees. The generated shock waves were of sufficient strength to produce turbulent boundary layer separation on the flat plate surface.
| Author | : Holger Babinsky |
| Publisher | : Cambridge University Press |
| Total Pages | : 481 |
| Release | : 2011-09-12 |
| Genre | : Technology & Engineering |
| ISBN | : 1139498649 |
Download Shock Wave-Boundary-Layer Interactions Book in PDF, ePub and Kindle
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.
| Author | : Earl C. Watson |
| Publisher | : |
| Total Pages | : 140 |
| Release | : 1969 |
| Genre | : Laminar boundary layer |
| ISBN | : |
Download Investigation of Laminar and Turbulent Boundary Layers Interacting with Externally Generated Shock Waves Book in PDF, ePub and Kindle
Laminar and turbulent boundary layer interactions with externally generated shock waves.
| Author | : L. Michael Freeman |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1975 |
| Genre | : Aerodynamic load |
| ISBN | : |
Download Experiments on the Interaction with a Turbulent Boundary Layer of a Skewed Shock Wave of Variable Strength at Mach 2.5 Book in PDF, ePub and Kindle
This report covers an experimental study of the interaction of a skewed shock wave of variable strength with a turbulent boundary layer at a working Mach number of 2.5. The skewed shock wave was generated by a vertical wedge whose angle was varied in increments of 1 degree or less between 6 and 18 degrees in order to cover the spectrum of interaction from below incipient to widespread separation. Measurements include pressure distributions and oil flow photographs. The incipient separation angle was found to be between 71/2 and 8 degrees. For large wedge angles there is the appearance in the oil flow photographs of an inflection within the separated region, suggesting the possible approach to a secondary separation. The extent of separation is relatively small for angles up to 10 degrees, but grows more rapidly for larger angles. (Author).
| Author | : Michael S. Holden |
| Publisher | : |
| Total Pages | : 185 |
| Release | : 1975 |
| Genre | : |
| ISBN | : |
Download Shock Wave Turbulent Boundary Layer Interaction in Hypersonic Flow Book in PDF, ePub and Kindle
A study is presented of the characteristics of transitional and turbulent layers, and regions of shock wave-turbulent boundary layer interaction in high Reynolds number hypersonic flow. An examination and correlation of skin friction, heat transfer and pressure measurements in laminar, transitional and turbulent boundary layers on sharp flat plates and cones are presented for the Mach range from 3 to 13 at wall-to-free stream temperature ratios from 0.1 to 0.4.
| Author | : C. Herbert Law |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1975 |
| Genre | : |
| ISBN | : |
Download Three-dimensional Shock Wave-turbulent Boundary Layer Interactions at Mach 6 Book in PDF, ePub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 23 |
| Release | : 1993 |
| Genre | : |
| ISBN | : |
Download The Structure of Turbulent Boundary Layers and Shock Wave Boundary Layer Interactions Book in PDF, ePub and Kindle
This report is the Final Technical Report for AFOSR Grant 89-0420, monitored by Dr James McMichael, for the period June 15, 1989 to October 14, 1992. Under this program, research was performed (1) to describe the structure of the large-scale motions in supersonic turbulent boundary layers, (2) to study the interaction of that turbulence with shock waves and strategies for controlling the interaction, (3) to differentiate between Mach and Reynolds number effects on turbulence structure in wall-bounded flows, and (4) to develop and implement new non-intrusive diagnostic techniques. The research is aimed at providing physical insight, and scaling information, for the development of turbulence models appropriate for supersonic shear layers. The primary experimental means used in these investigations were the Rayleigh scattering technique to study the instantaneous density field, the RELIEF line tagging method to study the instantaneous velocity field, and a dual hot-wire technique to obtain simultaneous velocity and density signals ... Boundary layers, Turbulence, Shock wave boundary layer interaction.
| Author | : Seymour M. Bogdonoff |
| Publisher | : |
| Total Pages | : 75 |
| Release | : 1985 |
| Genre | : |
| ISBN | : |
Download Three-Dimensional Shock Wave and Turbulent Boundary Layer Interactions Book in PDF, ePub and Kindle
An extensive experimental study of three-dimensional shock wave turbulent boundary layer interactions caused by shock generators defined solely by angles has been carried out at Mach 3. Sharp fins, sharp swept fins, swept wedges, and semi-cones have been used to generate a wide range of shock waves. The interaction of these waves with turbulent boundary layers has been investigated by surface flow visualization, mean surface static pressure distributions, flowfield surveys of total pressure and yaw, and several flowfield visualization techniques. Some exploratory high frequency surface pressure measurements have been carried out to evaluate the steadiness of these interactions. Scaling laws for both surface and flowfield features have been derived. Some limited studies were carried out at a Mach number of 2. A flowfield study has shown that the initial part of interactions caused by the same strength and geometrical shock wave generated by different shock generators are all similar. The 'footprints' of the interactions, as shown by surface flow visualization, can be categorized as approximately conical or cylindrical, and the boundaries between these two regions have been defined for both Mach 3 and Mach 2. There are still questions with regards to the detailed flowfield structures and physical mechanisms, but the three-dimensional interactions appeared to be less unsteady than that of two-dimensional separated flows.
