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| Author | : T. J. Garrison |
| Publisher | : |
| Total Pages | : |
| Release | : 1993 |
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| Author | : Seymour M. Bogdonoff |
| Publisher | : |
| Total Pages | : 39 |
| Release | : 1989 |
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The present report briefly reviews the work accomplished on the study of three-dimensional shock wave turbulent boundary layer interactions at a Mach 3. The work consisted of two major thrusts; 1) Modeling of the complex interaction and detailed experiments coordinated with extensive computations; and 2) Exploratory studies of control concepts for a 20 deg fin and crossing shock configurations. The completed works have been reported and are briefly reviewed. A brief resume is presented of incompleted results on complex interactions, new heat transfer techniques, initial spanwise boundary layer effects, and studies in a new Low Turbulence Variable Geometry facility. Keywords: Three-dimensional shock waves; Turbulent boundary layer; Supersonic flow fields; Surface heat transfer data. (edc).
| Author | : T. J. Garrison |
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| Total Pages | : |
| Release | : 1992 |
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| Author | : American Institute of Aeronautics and Astronautics |
| Publisher | : |
| Total Pages | : 654 |
| Release | : 2001 |
| Genre | : Aeronautics |
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| Author | : Holger Babinsky |
| Publisher | : Cambridge University Press |
| Total Pages | : 481 |
| Release | : 2011-09-12 |
| Genre | : Technology & Engineering |
| ISBN | : 1139498649 |
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 | : |
| Publisher | : |
| Total Pages | : 26 |
| Release | : 1986 |
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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.
| Author | : Earl C. Watson |
| Publisher | : |
| Total Pages | : 140 |
| Release | : 1969 |
| Genre | : Laminar boundary layer |
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Laminar and turbulent boundary layer interactions with externally generated shock waves.
| Author | : |
| Publisher | : |
| Total Pages | : 23 |
| Release | : 1993 |
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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 | : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development |
| Publisher | : |
| Total Pages | : 176 |
| Release | : 1998 |
| Genre | : Aerodynamics |
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| Author | : Doyle Knight |
| Publisher | : |
| Total Pages | : 76 |
| Release | : 1988 |
| Genre | : |
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This research describes continuing efforts in the analysis of 3-D shock wave turbulent boundary layer interactions. A significant research activity in 3-D hypersonic shock turbulent interactions is initiated to further develop and validate the theoretical model. The quasiconical free interaction principle is examined by simulation of two geometries -17.5 deg sharp fin and (30,60) swept compression corner (Mach 3) - selected to obtain similar shock strengths. The comparison with experimental data is good. It is confirmed that the differences caused by the particular geometry of the model appear only behind the inviscid shock wave. Continuing research on 3-D turbulent interaction control is focused on the effect of bleed and the simulation of flows past the double-fin configuration. The effect of suction is examined on a strong (fin angle=20 deg, Mach 3) and a weak interaction (8 deg, Mach 3). The overall effect of bleed is remarkably modest. Two double-fin configurations (4 x 4 and 8 x 8, Mach 3) are simulated. A study of the computed flowfield indicates that the first is a weak interaction. In contrast, the 8 x 8 configuration displays an interesting separated flowfield. An analysis of viscous and inviscid effects in a sharp fin and a swept corner flow indicates that the physics of both geometries are governed primarily by inviscid (pressure) effects. Viscous effects are of lower magnitude but are not restricted to the sublayer region. High speed flows; Viscous inviscid interactions; Boundary layer interactions; Computational fluid dynamics; Navier stokes equations; Turbulence.(mjm).
