Author: Brian R. SmithPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Prediction of Hypersonic Shock Wave Turbulent Boundary Layer Interactions with the K-l Two-equation Turbulence Model
Author: Brian R. SmithDocumentation of Two- and Three-dimensional Hypersonic Shock Wave/turbulent Boundary Layer Interaction Flows
Author: Marvin I. KussoyPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 32
Book Description
Prediction of Hypersonic Shock-wave/turbulent-boundary-layer Interaction Flows
Author: C.C. HorstmanA Computational Study on Shock Wave/turbulent Boundary Layer Interaction with Two-equation Turbulence Models
Author: Byong K. YoonNumerical Computations of Turbulence Amplification in Shock Wave Interactions
Author: Thomas A. ZangPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 40
Book Description
Turbulence Modeling for Hypersonic Flows
Author: Joseph G. MarvinTurbulence Compressibility Corrections
Author: Understanding and Predicting Shockwave and Turbulent Boundary Layer Interactions
Author: M. Pino MartinPublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 34
Book Description
Shockwave and turbulent boundary layer interactions produce intense localized pressure loads and heating rates that can have a dramatic influence on the drag and heating experienced by a high-speed vehicle, and can significantly impact fuel mixing and combustion in propulsion systems. The lack of standardized and traceable databases prevents the calibration of computational fluid dynamic models to accurately represent these critical flow phenomena. In this work we accomplished the development and validation against experiments at the same flow and boundary conditions of direct numerical simulations of shock and turbulent boundary layer interactions. We pioneered the development of a unique numerical capability that allows the accurate and detailed three-dimensional turbulence data at a reasonable turn-around time. In turn, parametric studies of fundamental flow physics are feasible, for the first time. By accurate, it is meant that the numerical uncertainty is within the experimental error.
Documentation of Two- And Three-Dimensional Hypersonic Shock Wave/Turbulent Boundary Layer Interaction Flows
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722182298
Category :
Languages : en
Pages : 28
Book Description
Experimental data for a series of two- and three-dimensional shock wave/turbulent boundary layer interaction flows at Mach 7 are presented. Test bodies, composed of simple geometric shapes, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface-pressure and heat-transfer distributions as well as limited mean-flow-field surveys in both the undisturbed and the interaction regimes. The data are presented in a convenient form for use in validating existing or future computational models of these generic hypersonic flows. Kussoy, Marvin I. and Horstman, Clifford C. Ames Research Center NCC2-452; RTOP 505-80-11...
Theoretical Investigation of Three-Dimensional Shock Wave-Turbulent Boundary Layer Interactions
Author: Doyle D. KnightPublisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
The focus of the research effort is the understanding of three-dimensional shock wave-turbulent boundary layer interactions. The approach uses the full mean compressible Navier-Stokes equations with turbulence incorporated through the algebraic turbulent eddy viscosity model of Baldwin and Lomax. During the present year of the research effort, the three-dimensional shock boundary layer interaction generated by a 10 deg sharp fin has been computed at Mach 3 for a Reynolds number 280000. These results, together with previous computations of the same configuration at Reynolds number = 930000, are compared with experimental data for pitot pressure and yaw angle. The agreement with the experimental data is good, and the theory accurately predicts the recovery of the boundary layer downstream of the interaction of Reynolds number = 280000. The computed flowfield is employed to analyze the structure of the 3-D interaction through contour plots of flow variables. Also, during the present year, the investigation of the 2-D turbulent supersonic compression corner at Mach 3 was completed. The relaxation modification to the Baldwin-Lomax model was found to yield reasonably accurate predictions of the upstream propagation of the surface for the Reynolds number range investigated. An additional computation at Mach 2 was performed, and the results were in general in agreement with the previous conclusions. (Author).