3 edition of Simulation of glancing shock wave and boundary layer interaction found in the catalog.
Simulation of glancing shock wave and boundary layer interaction
1989 by National Aeronautics and Space Administration, Ames Research Center, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va .
Written in English
|Series||NASA technical memorandum -- 102233.|
|Contributions||Ames Research Center.|
|The Physical Object|
|Pagination||10 p. :|
|Number of Pages||10|
A direct numerical simulation (DNS) on an oblique shock wave with an incident angle of ° impinging on a Mach supersonic turbulent boundary layer is :// An Experimental Study of the Interaction Between a Glancing Shock Wave and a Turbulent Boundary Layer," (). Computational Parametric Study of Sidewall-Compression Scramjet Inlet Performance at M" () A compressible vortex method with application to the interaction of an oblique shock wave with a boundary layer. Applied Numerical Mathematics , () Diffusing-vortex numerical scheme for solving incompressible navier-stokes :// Direct numerical simulation of turbulent boundary-layer flow over a circular-arc bump including shock/boundary-layer interactions has been carried out at Reynolds number Re δ 1 * = (based on the stagnation quantities and the inflow displacement thickness). The compressible Navier-Stokes equations were solved in generalized coordinates using a 4th-order central finite-difference-TVD
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Intramolecular cation transfer.
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Hung C. () Simulation of Glancing Shock Wave and Boundary Layer Interaction. In: Wesseling P. (eds) Proceedings of the Eighth GAMM-Conference on Numerical Methods in Fluid Mechanics. Notes on Numerical Fluid Mechanics (NNFM), vol A shock wave generated by one body, glancing across a boundary layer on another body, is a problem well suited to CFD capabilities.
This is one of the most common and important three-dimensional (3-D) inviscid/viscous interaction problems. The problem is so complicated that a purely theoretical approach is ahnost impossible. In early studies, Shock waves generated by sharp fins, glancing across a laminar boundary layer growing over a flat plate, are simulated numerically.
Several basic issues Get this from a library. Simulation of glancing shock wave and boundary layer interaction. [Ching-Mao Hung; Ames Research Center.] Kubota, H. A study of the interaction between a glancing shock wave and a turbulent boundary layer. PhD thesis, Cranfield Institute of Technology. Also: Investigations of three-dimensional shock wave boundary layer interactions.
Cranfield Institute of Technolgy, College of Aero. Rep. Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave. Glancing shock wave-turbulent boundary layer interaction with boundary layer suction. Experimental Investigation of a Cylinder-Induced Transitional Shock Wave-Boundary Layer :// Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gasdynamics and frequently a defining feature in high speed aerodynamic flowfields.
This is the first book devoted solely to the phenomenon and covers all flow regimes where SBLI's › Books › Engineering & Transportation › Engineering.
The shock wave/boundary layer interaction (SWBLI) occurs in supersonic and hypersonic practical flows such as scramjet inlets, re-entry vehicles, nozzles and launch vehicles, and it would result in boundary-layer thickening and can trigger separation and high-wall heat flux in the internal and external flow fields [, ], see Fig.
1, which increases pressure losses and distortion [4,5]. Whilst still challenging in terms of numerical methods, due to the simultaneous presence of shock waves and turbulence, both direct numerical simulation and large eddy simulations (LES) are useful tools to investigate fundamental issues of shock-wave/boundary-layer :// Computational fluid dynamics, Navier-Stokes equation, Turbulent boundary layer, Shock waves, Hypersonic inlets, Three dimensional flow, Turbulence models, Applications programs (Computers), Boundary layer flow, Boundary layer separation, Boundary layers, Compressor rotors, Computational grids, Corner flow, Engine inlets, Flow characteristics Book Search tips Selecting this option will search all publications across the Scitation platform Selecting this Low-frequency unsteadiness of shock-wave/boundary-layer interaction in an isolator with background waves “ Direct numerical simulation of impinging shock wave/turbulent boundary layer interaction at M = 2 Shock wave–boundary-layer interaction (SBLI) is a fundamental phenomenon in gas This is the ﬁrst book devoted solely to a comprehensive state-of-the-art explanation 7 Numerical Simulation of Hypersonic Shock Wave–Boundary-Layer Interactions Graham V.
Candler 8 Shock Wave Shock wave/turbulent boundary layer interaction and its control Progress in Aerospace Sciences, Vol. 22, No. 4 An assessment of numerical solutions Simulation of glancing shock wave and boundary layer interaction are used to study the so-called separated and Simulation of glancing shock wave and boundary layer interaction book boundary layer and to establish the existence or absence of the secondary separation.
The usual interpretations of the flow field from previous studies and new interpretations arising from the present simulation are The interaction of a shock wave with a turbulent boundary layer can drastically change aerodynamic loads, alter combustion processes, and produce intense local heating, buffeting, and loss of control.
Shock-wave/ boundary-layer interactions have therefore been the subject of extensive :// Pirozzoli, S., Grasso, F.: Direct numerical simulation of impinging shock wave/turbulent boundary layer interaction at M= Phys.
Fluids 18 () Google Scholar Search within book. Front Matter. Simulation of Glancing Shock Wave and Boundary Layer Interaction. Ching-mao Hung. Pages Development of the MZM numerical method for 3D boundary layer with interaction on complex configurations. Lazareff, J.
le Balleur. Pages Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number 22 June | Journal of Fluid Mechanics, Vol. Numerical analysis of shock wave and supersonic turbulent boundary interaction between adiabatic and cold walls Numerical Investigation of a Normal Shock Wave Boundary Layer Interaction in a Aspect Ratio Test Section.
Mortaza Mani; 2 January Numerical simulation of shock trains in a 3D channel. Glancing shock wave-turbulent boundary layer interaction with boundary layer :// Shang, J. S Hankey, W. L Law, C. H Numerical simulation of shock wave/turbulent boundary-layer interaction AIAA J 14 Chapman, D.
R Kuhen, D. M Larson, H. K Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition NACA TN Shock-vortex shear-layer interaction in the transonic flow around a supercritical airfoil at high Reynolds number in buffet conditions.
Simulation of shock wave buffet and its suppression on an OAT15A supercritical airfoil by IDDES. Analysis of multiple weak glancing shock boundary layer Turbulent boundary layers, especially at high Reynolds numbers, are very sensitive to wall is because any roughness element that protrudes through the viscous sublayer modifies the law of the wall.
The effect of wall roughness on the boundary layer depends on the size, shape, and spacing of the :// Numerical Simulation on the Shock Wave/Boundary Layer Interaction with Heating/Cooling Effect Gabi Ben-Dor, Ozerlgra in his book mentioned that the wall temperature level would have subtle influence on incoming boundary layer.
Recently,  in experimentally investigated the wall- temperature effects on the behaviour of a Large eddy simulation of shock boundary layer interaction in a transonic internal flow Moroianu, Dragos LU; Caraeni, Doru LU and Fuchs, Laszlo LU () 43rd AIAA Aerospace Sciences Meeting and Exhibit p Mark; Abstract The paper presents a study of the dynamics of non-stationary shock wave and its interaction with the boundary layer in a transonic flow inside a channel with a :// Interaction between a shock wave and an unseparated turbulent boundary layer is considered.
The method of matched asymptotic expansions is used, with solutions valid in the double limit as Reynolds number tends to infinity and Mach number tends to unity. The shock is weak enough that interaction effects can be considered as perturbations to the undisturbed flow; the case Babinsky, H.
& Harvey, J. (Eds) Shock Wave–Boundary-Layer Interactions. Cambridge University Press. Burcham, F. & Nugent, J. Local flow field around a pylon-mounted dummy ramjet engine on the x for Mach numbers to "This is the first book devoted solely to the phenomenon of Shock Wave Boundary Layer Interactions and covers all flow regimes where SBLI's occur"--Provided by publisher.
"Shock Wave/Boundary Layer Interaction (SBLI) is a fundamental phenomenon in gas dynamics and frequently a defining feature in high speed aerodynamic :// In book: Direct and Large Eddy Simulation XII, pp the fundamental mechanisms of the shock-wave/boundary-layer interaction (SWBLI).
first reflected interaction is present in the The crossing shock/boundary-layer experiment was configured by using two shock generator plates that span the tunnel test section. The cm long shock generators arranged symmetrically produce oblique shocks which cross each other on the centerline.
The interaction of these shocks with the naturally occurring incoming flow boundary layer on Using a nanoparticle-based planar laser-scattering technique and supersonic particle image velocimetry, we investigated the effects of micro-ramp control on incident shockwave and boundary-layer interaction (SWBLI) in a low-noise supersonic wind-tunnel with Mach number and Reynolds number R θ = High spatiotemporal resolution wake structures downstream of the micro-ramps were A spatially developing supersonic adiabatic flat plate boundary layer flow (at M ∞ = and Re θ ≈) is analyzed by means of direct numerical simulation.
The numerical algorithm is based on a mixed weighted essentially nonoscillatory compact-difference method for the three-dimensional Navier–Stokes equations. The main objectives are to assess the validity of Morkovin’s hypothesis Get this from a library. 3-D Navier-Stokes analysis of crossing, glancing shocks/turbulent boundary layer interactions.
[D R Reddy; United States. National Aeronautics and Space Administration.] Shock Wave-Boundary-Layer Interactions - Ebook written by Holger Babinsky, John K. Harvey.
Read this book using Google Play Books app on your PC, android, iOS devices. Download for offline reading, highlight, bookmark or take notes while you read Shock Wave-Boundary-Layer :// An analysis for predicting the interaction of a steady oblique shock wave and a planar mixing region is presented.
Specifically, an equation for the shock curvature was obtained from the shock wave and isentropic wave difference equations which govern the shock 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.
This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI The interaction between an impinging oblique shock–wave and a laminar boundary layer on a flat plate is investigated using direct numerical simulations.
The two–dimensional separation bubble resulting from the shock boundary layer interaction (SBLI) at freestream Mach number of for the approach flow is investigated in :// A delayed-detached-eddy simulation (DDES) is conducted with a low diffusion E-CUSP (LDE) scheme and fifth-order WENO scheme for the inviscid fluxes and 4th order central differencing scheme for viscous terms to study the shock/wave turbulent boundary layer :// Book Search tips Selecting this option will search all publications across the Scitation platform Selecting this option will search all publications for the Publisher “ Fifty years of shock-wave/boundary-layer interaction research: “ Large-eddy simulation of shock-wave/turbulent-boundary-layer interaction,” J.
Fluid Mech. A numerical analysis is performed to explore the high altitude and high Mach flight on the effect of wall boundary layer loss in the compressor. The accuracy for solution results by the application of the similarity criterion and parameter definition of the air inlet is compared with the existing experimental test result.
The results indicate that the radial adverse pressure gradient in the User Tools. Cart. Sign In. As seen in Sectionwhen separation occurs, the smearing of the shock system and splitting of the compression achieved by the interaction reduce the wave drag, or the efficiency loss, due to the shock.
On the other hand, the momentum loss in a separated boundary layer is far more important than that through an attached boundary layer Turbulent transonic flow past flattened aerodynamic surfaces is investigated numerically using the RANS equations.
The study is focused on: (a) instability of the entire flow structure which eventually results in flow bifurcations, (b) a buffet onset caused by instability of the shock wave/ boundary layer interaction. For a symmetric airfoil at zero angle of attack, computations reveal both An experimental investigation was made to study the interaction between an incident oblique shock wave and a turbulent boundary layer on a solid surface downstream of a porous surface with air