Finite-difference Solutions of the Turbulent Interacting Supersonic Boundary-layer Equations, Including Separation Effects PDF Download
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Author: Stephen Donald Bertke
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 392
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Book Description
Author: Stephen Donald Bertke
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 392
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Book Description
Author: S. D. Bertke
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
A numerical algorithm is presented for the solution of the supersonic interacting turbulent boundary layer equations including separation effects. A representative eddy viscosity model is used to describe turbulent stress. Mach 3 cold wall flow up a compression ramp at (Re sub infinity) = 100,000 is used to demonstrate the fundamental technique. The numerical algorithm developed is a relaxation technique taylored after the implicit alternating direction method employed for boundary value partial differential equation systems. (Author).
Author: Michael J. Werle
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
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Book Description
The boundary-layer equations including the effects of interaction with a supersonic mainstream are solved using an implicit finite difference scheme. The free interaction process is studied extensively and favorable comparisons made with experimental data, expirical correlations, and analytical results. Solutions are presented for shockwave and compression ramp induced separations and reattachments for a Mach 3 mainstream at moderate and cold wall temperatures. Surprisingly little overheating is observed aft of reattachment. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1460
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Bernhard Stoevesandt
Publisher: Springer Nature
ISBN: 3030313077
Category : Technology & Engineering
Languages : en
Pages : 1495
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Book Description
This handbook provides both a comprehensive overview and deep insights on the state-of-the-art methods used in wind turbine aerodynamics, as well as their advantages and limits. The focus of this work is specifically on wind turbines, where the aerodynamics are different from that of other fields due to the turbulent wind fields they face and the resultant differences in structural requirements. It gives a complete picture of research in the field, taking into account the different approaches which are applied. This book would be useful to professionals, academics, researchers and students working in the field.
Author: M. J. Werle
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
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Book Description
An efficient numerical solution algorithm is presented for solving the interacting supersonic laminar boundary layer problem. The method employs a time dependent approach with the alternating direction implicit (ADI) scheme and directly accounts for the necessary downstream boundary condition. Solutions are presented for (M sub infinity) = 3 cold wall boundary layer flow over a family of expansion and compression ramps including several cases with regions of reverse flow. Good comparison is given with experimental data and Navier Stokes solutions for (M sub infinity) = 4, adiabatic wall, separated flow up a ten degree compression ramp. (Author).
Author: G. D. Senechal
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 61
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Book Description
A numerical study has been made of the nature of the solution to the supersonic boundary-layer equations when the flow separates from the surface. To this end, implicit finite difference solutions t the governing equations are obtained for linearly and quadratically retarded flows over flat plates for a Mach number range of 2 to 15. Both extremely hot and cold wall conditions are considered. Also, solutions for flow on a compression ramp are obtained with and without including the boundary layer's free interaction with the local freestream. The results of this study indicate that non-interacting flows are singular at separation and that free interaction effects reduces singularity. An alternate means of numerically smearing out the singularity and proceeding past separation is also presented.
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 594
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Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 592
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Book Description
Author: James Edward Carter
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 90
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Book Description
Numerical solutions have been obtained for the supersonic, laminar flow over a two-dimensional compression corner. These solutions were obtained as steady-state solutions to the unsteady Navier-Stokes equations using the finite-difference method of Brailovskaya, which has the second-order accuracy in the spatial coordinates. Good agreement was obtained between the computed results and the wall pressure distributions measured experimentally by Lewis, Kubota, and Lees for Mach numbers of 4 and 6.06, and respective Reynolds numbers, based on free-stream conditions and the distance from the leading edge to the corner, of 6.8 x 104 and 1.5 x 105. In those calculations, as well as in others, sufficient resolution was obtained to show the streamline pattern in the separation bubble. Upstream boundary conditions to the compression-corner flow were provided by numerically solving the unsteady Navier-Stokes equations for the flat-plate flow field, beginning at the leading edge. The compression-corner flow field was enclosed by a computational boundary with the unknown boundary conditions supplied by extrapolation from internally computed points. Numerical tests were performed to deduce that the magnitude of the errors introduced by the extrapolation was small. Calculations were made to show the effect of ramp angle and wall suction on the interaction flow field. The pressure distributions obtained in the present calculations, including a case of incipient separation, were plotted together by using the free-interaction scaling of Stewartson and Williams. A good correlation of the numerical results was found, but only fair agreement was found between this correlation and the universal pressure distribution found numerically by Stewartson and Williams.
