Author: Thierry MaederPublisher:
ISBN: 9783183394074
Category :
Languages : en
Pages : 119
Book Description
Numerical Investigation of Supersonic Turbulent Boundary Layers
Author: Thierry MaederPublisher:
ISBN: 9783183394074
Category :
Languages : en
Pages : 119
Book Description
Numerical Investigation of Compressible Turbulent Boundary Layers
Author: Muhammad Farrukh ShahabPublisher: LAP Lambert Academic Publishing
ISBN: 9783848415151
Category :
Languages : en
Pages : 228
Book Description
As a prerequisite for relevant model development and improvement of design methodologies for supersonic vehicles, this study aims at investigating the influence of wall heat-transfer and shock interaction on the turbulence structure of supersonic boundary layers. Incipient separation conditions and two different wall thermal boundary conditions (adiabatic and cold) are considered. The analysis focuses on the evolution of mean and turbulent flow properties along the interaction region and in the relaxation region downstream of the shock-system. The strong influence of the mean pressure gradient is quantified through the analysis of mean flow profiles and boundary layer integral parameters. The anisotropic amplification of turbulent quantities through the interaction region is characterized and the turbulent events associated with the modification of the turbulence structure of the perturbed boundary layer are identified. The mean and turbulent thermal fields are shown to be strongly modified by the wall cooling which significantly dampens more particularly the turbulent thermal quantities levels across the boundary layer.
יסודות המילים
Author: Interacting Supersonic Turbulent Boundary Layers Over a Two-dimensional Protuberance
Author: Arnold PolakPublisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 38
Book Description
The report presents a numerical study of attached interacting supersonic turbulent boundary layers over a two-dimensional protuberance. Results are presented in terms of surface pressure, heat transfer and skin-friction distributions. These results indicate a strong effect of the size of the protuberance, Mach number, but a weak effect of Reynolds number and the ratio of wall-to-recovery temperature. The peak heating rates from a set of test cases compare well to a semi-empirical prediction method. In contradistinction to the laminar case, the turbulent recovery zone downstream of the protuberance is very short. (Author).
Shock Wave-Boundary-Layer Interactions
Author: Holger BabinskyPublisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
Book Description
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.
A Numerical Investigation of Supersonic Nozzle Boundary Layer Transition
Author: Laura L. PauleyA Numerical Investigation of Supersonic Turbulent Shear Layers
Author: Choong K. OhInvestigation of Supersonic Boundary Layer Transition and Turbulent Structure
Author: Alexander J. SmitsPublisher:
ISBN:
Category : Rayleigh scattering
Languages : en
Pages : 40
Book Description
Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721518654
Category :
Languages : en
Pages : 38
Book Description
The results from direct numerical simulations of a spatially evolving, supersonic, flat-plate turbulent boundary-layer flow, with free-stream Mach number of 2.25 are presented. The simulated flow field extends from a transition region, initiated by wall suction and blowing near the inflow boundary, into the fully turbulent regime. Distributions of mean and turbulent flow quantities are obtained and an analysis of these quantities is performed at a downstream station corresponding to Re(sub x)= 5.548 x10(exp 6) based on distance from the leading edge. Gatski, T. B. and Erlebacher, G. Langley Research Center NASA/TM-2002-211934, NAS 1.15:211934, L-18225
Author: K. E. Williams