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Reynolds averaged Navier-Stokes computations of transonic flows The-state-of-the-art

01 Jan 1982-
TL;DR: In this paper, the state of the art in computer simulations for transonic flowfields requiring solutions for the Navier-Stokes equations is assessed and the choice of coordinate systems and dependent variables for simulating the flow around airfoils is discussed, with particular attention to curvilinear coordinates.
Abstract: The state of the art in computer simulations for transonic flowfields requiring solutions for the Navier-Stokes equations is assessed. It is noted that current simulations of transonic flowfields require comparisons with experimental results because the simulations are not free from discretization errors. Cases of turbulence are treated with weighted variables in a time-averaged scheme to yield Reynolds averaged Navier-Stokes equations. The turbulence is modeled in a first-order approach with a Reynolds stress tensor or a second-order approach where the tensor is obtained from the Navier-Stokes equations. The choice of coordinate systems and dependent variables for simulating the flow around airfoils is discussed, with particular attention to curvilinear coordinates. The determinations of boundary conditions is examined, along with numerical methods related to physical phenomena
Citations
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Journal ArticleDOI
TL;DR: In this paper, les regions tridimensionnelles sont mieux traitees par fragmentation du champ en sous-regions avec generation de grilles dans chaque sousregion.
Abstract: Revue des differentes methodes. On montre que les regions tridimensionnelles sont mieux traitees par fragmentation du champ en sous-regions avec generation de grilles dans chaque sous-region. Interet des grilles adaptatives couplees a des solutions physiques

153 citations

Journal ArticleDOI
Paul Kutler1
TL;DR: The advantages and disadvantages of analytical methods, computational procedures, and experimentation for aerodynamic design are summarized in Fig. 1 as discussed by the authors, where the advantages of each of them are discussed.
Abstract: O heighten his understanding of the fluid dynamics and aerodynamics pertinent to the early stages of the atmospheric flight-vehicle design process, the aerodynamicist has at his disposal three standard tools: analytical methods, computational procedures, and experimentation. Some of the advantages and disadvantages of each design tool are summarized in Fig. 1. Analytical methods provide quick, closed-form solutions, but they require unduly restrictive assumptions, can treat only simple configurations, and capture only the idealized aerodynamics. Through experimentation, representative or actual configurations can be tested and representative and complete aerodynamic data can be produced. Experimentation is costly, however, both in terms of the model and actual test time. In addition, the limited conditions that can be attained in wind tunnels restrict the scope of ex

68 citations

Journal ArticleDOI
TL;DR: An explicit multistage Runge-Kutta type of time-stepping scheme is used to solve the three-dimensional, compressible, thin-layer Navier-Stokes equations.
Abstract: An explicit multistage Runge-Kutta type of time-stepping scheme is used to solve the three-dimensional, compressible, thin-layer Navier-Stokes equations A finite-volume formulation is employed to facilitate treatment of complex grid topologies encountered in three-dimensional calculations Convergence to steady state is expedited through the use of acceleration techniques Further numerical efficiency is achieved through yectorization of the computer code The accuracy of the overall scheme is evaluated by comparing the computed solutions with the experimental data for a finite wing under different test conditions in the transonic regime A grid refinement study is conducted to estimate the grid requirements for adequate resolution of salient features of such flows

57 citations

Journal ArticleDOI
Eli Turkel1
TL;DR: In this article, recent progress in computational methods for time dependent fluid dynamics is presented with the emphasis on advances applicable to large scale systems with the connection between the numerics and the physics of the code stressed All aspects of a working code are discussed including initialization, boundary conditions, grid generation in addition to algorithmic advances.

38 citations

01 Feb 1987
TL;DR: The experimental evidence for the effects of rain, insects, and ice on airfoil performance is examined in this article, where the extent to which the available information can be incorporated in a calculation method in terms of change of shape and surface roughness is discussed.
Abstract: The experimental evidence for the effects of rain, insects, and ice on airfoil performance are examined. The extent to which the available information can be incorporated in a calculation method in terms of change of shape and surface roughness is discussed. The methods described are based on the interactive boundary layer procedure of Cebeci or on the thin layer Navier Stokes procedure developed at NASA. Cases presented show that extensive flow separation occurs on the rough surfaces.

25 citations

References
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Book
01 Jan 1972
TL;DR: In this paper, the authors present a reference record created on 2005-11-18, modified on 2016-08-08 and used for the analysis of turbulence and transport in the context of energie.
Abstract: Keywords: turbulence ; transport ; contraintes ; transport ; couche : limite ; ecoulement ; tourbillon ; energie Reference Record created on 2005-11-18, modified on 2016-08-08

8,276 citations

Journal ArticleDOI
TL;DR: In this article, the local turbulent viscosity is determined from the solution of transport equations for the turbulence kinetic energy and the energy dissipation rate, and the predicted hydrodynamic and heat-transfer development of the boundary layers is in close agreement with the measured behaviour.

3,999 citations

Proceedings ArticleDOI
01 Jan 1978
TL;DR: In this article, an algebraic turbulence model for two-and three-dimensional separated flows is specified that avoids the necessity for finding the edge of the boundary layer, and compared with experiment for an incident shock on a flat plate, separated flow over a compression corner, and transonic flow over an airfoil.
Abstract: An algebraic turbulence model for two- and three-dimensional separated flows is specified that avoids the necessity for finding the edge of the boundary layer. Properties of the model are determined and comparisons made with experiment for an incident shock on a flat plate, separated flow over a compression corner, and transonic flow over an airfoil. Separation and reattachment points from numerical Navier-Stokes solutions agree with experiment within one boundary-layer thickness. Use of law-of-the-wall boundary conditions does not alter the predictions significantly. Applications of the model to other cases are contained in companion papers.

3,701 citations

MonographDOI
01 Jan 1972
TL;DR: In this article, the authors discuss the Reynolds equations and estimate of the Reynolds stress in the kinetic theory of gases, and describe the effects of shear flow near a rigid wall.
Abstract: This chapter contains sections titled: The Reynolds equations, Elements of the kinetic theory of gases, Estimates of the Reynolds stress, Turbulent heat transfer, Turbulent shear flow near a rigid wall

3,270 citations

MonographDOI
01 Jan 1972
TL;DR: In this article, the probability density, Fourier transforms and characteristic functions, joint statistics and statistical independence, Correlation functions and spectra, the central limit theorem, and the relation functions are discussed.
Abstract: This chapter contains sections titled: The probability density, Fourier transforms and characteristic functions, Joint statistics and statistical independence, Correlation functions and spectra, The central limit theorem

3,260 citations