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U. Mehta

Bio: U. Mehta is an academic researcher. The author has contributed to research in topics: Hydrodynamic stability & Reynolds stress. The author has an hindex of 1, co-authored 1 publications receiving 24 citations.

Papers
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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

24 citations


Cited by
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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