Numerical Simulation of Supersonic Turbulent Boundary Layer Flow Under the Influence of Mild Pressure Gradients PDF Download
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Author: Eric Thomas Fick
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
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Author: Eric Thomas Fick
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
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Author: E. T. Fick
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Eric Thomas Fick
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 276
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Author: Alexander J. Smits
Publisher: Springer Science & Business Media
ISBN: 0387263055
Category : Science
Languages : en
Pages : 418
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Book Description
A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Author: A. J. Laderman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 190
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Book Description
Measurements of mean flow profiles at several streamwise locations in a supersonic turbulent boundary layer growing under a continuous adverse pressure gradient are reported. Tests were performed at a freestream Mach number of 3, for an adiabatic wall, using two curved ramps designed to produce constant pressure gradient flows. The velocity profile data, when transformed to incompressible coordinates, are in good agreement with Coles universal 'wall-wake' velocity profile and they indicate that the boundary layer is in local equilibrium and essentially independent of upstream history. In addition, the Coles wake parameters and Clauser shape factors, characterizing the transformed profiles, are in accord with the results of low speed correlations of adverse pressure gradient flows. The turbulent transport terms were extracted from the mean flow field data and indicate that for a given ramp, the profile of turbulent shear stress normalized by the wall shear, versus distance from the surface, normalized by the local boundary thickness, is severely distored by the pressure gradient although it is apparently insensitive to local conditions.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 26
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721518654
Category :
Languages : en
Pages : 38
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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: Maurice Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 686
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An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Author: Maurice Tucker
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 86
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Book Description
As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.
Author: D. K. Patel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Book Description
