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Interaction between laminar boundary layers and shock waves with separation of flow

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Published by University of Minnesota in St. Paul, Minnesota .
Written in English

Subjects:

  • Aeronautics

Book details:

Edition Notes

ContributionsUniversity of Minnesota
The Physical Object
Pagination1 v. :
ID Numbers
Open LibraryOL25126228M

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  7. Interaction involving a normal shock at M = After Seddon (). INTERACTIONS BETWEEN SHOCK WAVES AND BOUNDARY LAYERS pressure and flow direction downstream of this intersection, an incoming "weak" oblique shock is generated, and a vortex sheet with a rapid entropy rise across it runs downstream from the ://   Part A: Laminar-turbulent transition. Laminar-turbulent transition strongly affects the wall heat flux of high speed vehicles. The first part of this Lecture is devoted to the description and the modelling of some transition mechanisms. The transition process dominated by the amplification of unstable waves is considered first, with emphasis on the linear stability :// The interaction of an oblique shock with a laminar boundary layer on an adiabatic flat plate is analysed by solving the Navier-Stokes equations numerically. Mach numbers range from to and Reynolds numbers range from 10 5 to 6 × 10 :// Separation depends on whether the boundary layer, just upstream of the incident shock, is laminar, transitional, or turbulent. Laminar boundary layers separate much more readily than turbulent layers; however, turbulent layers predominate in real flows. If the upstream boundary layer is laminar, the interaction, with or without separation

  Interactions between Normal Shock Waves Turbulent Boundary Layers By G. E. GADD, Ph.D2 OF.'THE AERODYNAMICS DIVISION, N.P.L. and Reports and Memoranda No. t February, i96z Summary. A theory, involving a simple new method for turbulent boundary layers, is presented 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. no. The separation length of shock wave/boundary layer interaction (SWBLI) was studied by a numerical method, which was validated by experimental results. The computational domain was two-dimensional (2-D). The flow field was an incident oblique shock interacting with a turbulent boundary layer on a flat adiabatic plate. According to the simulation data, the dependency of the separation length on   , “ The Interaction of an Oblique Shock Wave with a Laminar Boundary Layer Revisited. An Experimental and Numerical Study,” Journal of Fluid Mechanics, Vol. , April , pp. –

  Unsteadiness of axisymmetric shock-dominated hypersonic laminar separated flow over a double cone is studied for the first time using a combination of time accurate Direct Simulation Monte Carlo (DSMC) calculations, linear global instability analysis, and momentum potential theory (MPT). Various direct numerical simulations were carried out of a shock-wave/laminar-boundary-layer interaction (SWBLI). Three-dimensional unsteady Navier–Stokes equations are numerically solved with an implicit dual time stepping for the temporal algorithm and high-order AUSMPW+ scheme for   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 :// To investigate this streamwise motion, the interaction between a laminar boundary layer and an oblique shock has been studied using DNS. The shock conditions (Mach number, shock angle