4 edition of Simulation of glancing shock wave and boundary layer interaction found in the catalog.
Simulation of glancing shock wave and boundary layer interaction
Published
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
Edition Notes
| Statement | Ching-Mao Hung. |
| Series | NASA technical memorandum -- 102233. |
| Contributions | Ames Research Center. |
| The Physical Object | |
|---|---|
| Format | Microform |
| Pagination | 10 p. |
| Number of Pages | 10 |
| ID Numbers | |
| Open Library | OL16140340M |
Babinsky, H. & Harvey, J. K. (Eds) Shock Wave–Boundary-Layer Interactions. Cambridge University Press. Burcham, F. W. & 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
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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 unseparated 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 [13]in his book mentioned that the wall temperature level would have subtle influence on incoming boundary layer.
Recently, [14] in experimentally investigated the wall- temperature effects on the behaviour of a
