Numerical Simulation of Crossing Shock/turbulent Boundary Layer Interaction at Mach 8.3 PDF Download
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Author: N. Narayanswami
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: N. Narayanswami
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: M. Pino Martin
Publisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 34
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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.
Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781729357682
Category :
Languages : en
Pages : 48
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Most flows of aerodynamic interest are compressible and turbulent. However, our present knowledge on the structures and mechanisms of turbulence is mostly based on incompressible flows. In the present work, compressibility effects in turbulent, high-speed, boundary layer flows are systematically investigated using the Direct Numerical Simulation (DNS) approach. Three-dimensional, time-dependent, fully nonlinear, compressible Navier-Stokes equations were numerically integrated by high-order finite-difference methods; no modeling for turbulence is used during the solution because the available resolution is sufficient to capture the relevant scales. The boundary layer problem deals with fully-turbulent compressible flows over flat geometries. Apart from its practical relevance to technological flows, turbulent compressible boundary layer flow is the simplest experimentally realizable turbulent compressible flow. Still, measuring difficulties prohibit a detailed experimental description of the flow, especially in the near-wall region. DNS studies provide a viable means to probe the physics of compressible turbulence in this region. The focus of this work is to explore the paths of energy transfer through which compressible turbulence is sustained. The structural similarities and differences between the incompressible and compressible turbulence are also investigated. The energy flow patterns or energy cascades are found to be directly related to the evolution of vortical structures which are generated in the near-wall region. Near-wall structures, and mechanisms which are not readily accessible through physical experiments are analyzed and their critical role on the evolution and the behavior of the flow is documented extensively. Biringen, Sedat and Hatay, Ferhat F. Unspecified Center NAG1-1472...
Author: K. E. Williams
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
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Author: Thomas A. Zang
Publisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 40
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Author: E. Blosch
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Category :
Languages : en
Pages :
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Author: Jason T. Lachowicz
Publisher:
ISBN:
Category :
Languages : en
Pages : 148
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Author: John Arthur Boles
Publisher:
ISBN:
Category :
Languages : en
Pages : 140
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Keywords: hybrid turbulence model, high-speed flow, flow modeling, shockwave boundary layer interaction, turbulent boundary layer, CFD, LES, turbulence, turbulence modeling.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 144
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Author: National Aeronautics and Space Adm Nasa
Publisher:
ISBN: 9781729362488
Category :
Languages : en
Pages : 54
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Experimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat-plate test bed, 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 mean flow-field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows. The data are also on a 3.5-inch diskette included and are available through E-mail. Kussoy, M. I. and Horstman, K. C. Ames Research Center...
