Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows
![Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows](https://ardhindie.com/assets/pdf.png)
DOWNLOAD
Download Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows
DOWNLOAD
Author : David S. Dolling
language : en
Publisher:
Release Date : 1977
Three Dimensional Shock Wave Turbulent Boundary Layer Interactions A Preliminary Analysis Of Blunted Fin Induced Flows written by David S. Dolling and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with categories.
An extensive experimental investigation has been made of three-dimensional blunted fin-induced shock wave turbulent boundary layer interactions. Surface pressures, heat transfer rate distributions and oil streak patterns were obtained over a range of fin bluntnesses and incidences for two different incoming boundary layers. These incoming boundary layers had mean thicknesses in the ratio of approximately 4:1. Preliminary analysis of these data indicates that, over a large region of the interaction, the property distributions collapse using purely geometric parameters. In contrast to its two-dimensional counterpart, which is a highly Reynolds number dependent viscous phenomenon, the present results seem to indicate that the three-dimensional case is primarily inviscid.
Experimental Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction An Exploratory Study Of Blunt Fin Induced Flows
DOWNLOAD
Author : David S. Dolling
language : en
Publisher:
Release Date : 1980
Experimental Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction An Exploratory Study Of Blunt Fin Induced Flows written by David S. Dolling and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with categories.
An experimental study of three-dimensional (3-D) shock wave turbulent boundary layer interaction has been carried out. Interactions generated by fin models having sharp and hemi-cylindrically blunted leading edges have been studied. The emphasis in this particular study was twofold. First, the influence of incoming turbulent boundary layer thickness delta on the streamwise, spanwise and vertical scaling of the interaction was examined. Turbulent boundary layers varying in thickness from .127 cm (.05 in.) to 2.27 cm (0.89 in.) were used. In addition, a study has been conducted to examine the effects of the ratio D/delta (where D is the blunt fin leading edge diameter) on the interaction properties and scaling. Second, an investigation has been started to examine the unsteady shock wave-boundary layer structure and the resulting high frequency, large amplitude pressure fluctuations which occur ahead of and around the blunt fin leading edge. This is an area which in the past has been largely ignored, yet has important implications, since it is not clear that any mean surface property or flowfield measurements have any real physical significant. To date, measurement techniques and computer software have been developed and exploratory measurements made in the undisturbed turbulent boundary layer and also on the plane of symmetry ahead of the blunt fin.
Shock Wave Boundary Layer Interactions
DOWNLOAD
Author : Holger Babinsky
language : en
Publisher: Cambridge University Press
Release Date : 2011-09-12
Shock Wave Boundary Layer Interactions written by Holger Babinsky and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-09-12 with Technology & Engineering categories.
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.
Experimental Study Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction Scaling Of Sharp And Blunt Fin Induced Flowfields
DOWNLOAD
Author : David S. Dolling
language : en
Publisher:
Release Date : 1980
Experimental Study Of Three Dimensional Shock Wave Turbulent Boundary Layer Interaction Scaling Of Sharp And Blunt Fin Induced Flowfields written by David S. Dolling and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1980 with categories.
An experimental study of three-dimensional (3-D) shock wave turbulent boundary layer interaction has been carried out. Interactions generated by fin models having sharp and hemi-cylindrically blunted leading edges have been studied. Tests have been made using incoming turbulent boundary layer varying in thickness in the ratio of about 4:1. Extensive surface property measurements have been made on the test surface on which the incoming boundary layer developed and on the fin itself. All of these tests were carried out at a nominal freestream Mach number of 3, a freestream unit Reynolds number of about 63 million per meter, and under approximately adiabatic wall conditions. The emphasis in the study reported on in this paper was on two main areas. First, to determine the key geometric and/or flow parameters controlling the overall scaling and characteristics of both blunt and sharp fin-induced interactions. Second, to identify the conditions under which both blunt and sharp fins induced interactions have the same local scale and characteristics. (Author).
Scientific And Technical Aerospace Reports
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1973
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1973 with Aeronautics categories.
Three Dimensional Shock Wave And Turbulent Boundary Layer Interactions
DOWNLOAD
Author : Seymour M. Bogdonoff
language : en
Publisher:
Release Date : 1985
Three Dimensional Shock Wave And Turbulent Boundary Layer Interactions written by Seymour M. Bogdonoff and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1985 with categories.
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.
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 4
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1986
Theoretical Investigation Of Three Dimensional Shock Wave Turbulent Boundary Layer Interactions Part 4 written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1986 with categories.
A theoretical model consists of the Reynolds-averaged 3-D compressible Navier-Stokes equations, with turbulence incorporated using the algebraic turbulent eddy viscosity model of Baldwin and Lomax, This year research efforts focused on both 2-D and 3-D turbulent interactions. A theoretical model was examined for a series of separated 2-D compression corner flows at Mach 2 and 3. Calculations were performed for four separate compression corners using 2-D compressible Navier-Stodes conde with MacCormack's hybrid algorithm. Results were compared to earlier computations using the Beam-Warming algorithm, and recent experiment data for turbulent Reynolds stresses. Calculated Reynolds stresses were observed to differ significantly from experimental measurements due to the inability of the turbulence model to incorporate the multiple scale effects of the turbulence structure downstream of reattachment. Computed results using the MacCormack hybrid algorithm were observed to be insensitive to the Courant number. The 3-D turbulence interactions research concentrated on the 3-D sharp fin and on the 3-D swept compression corner. In the former case, the computed flowfield for the 20 deg sharp fin at Mach 3 and a Reynolds number of 930,000 was compared with the calculated results of Horstman (who used the Jones-Launder turbulence model) and experimental data of the Princeton Gas Dynamics Lab. Overall comparison with experiment was very good.
Star
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1973
Star written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1973 with Aeronautics categories.
Computation Of Three Dimensional Shock Wave And Boundary Layer Interactions
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1985
Computation Of Three Dimensional Shock Wave And Boundary Layer Interactions written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1985 with categories.
A Three Dimensional Study Of Fin Induced Shock Wave Turbulent Boundary Layer Interaction
DOWNLOAD
Author : D. S. Dolling
language : en
Publisher:
Release Date : 1977
A Three Dimensional Study Of Fin Induced Shock Wave Turbulent Boundary Layer Interaction written by D. S. Dolling and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with categories.
Surface pressure distributions and oil streak patterns have been measured in the three-dimensional flowfield caused by the interaction of a skewed shock wave with a two-dimensional turbulent boundary layer. The boundary layer was developing on a 45 deg sweptback, sharp leading edged plate. Tests were made at a freestream Mach number of 2.95, a freestream unit Reynolds number of 63,000,000/m (1,600,000/in), a stagnation temperature of about 265 K and at near adiabatic wall temperature. Measurements have been made for generator angles in the range 0 to 12 deg in 2 deg increments. These measurements represent the first phase of a study which will include heat transfer measurements and details of the flowfield. The measured data are presented and compared with data obtained under the same shock wave conditions but with a different boundary layer. (Author).