A Method of Direct Calculation of Compressible Turbulent Skin Friction and Heat Transfer in Three-Dimensional Boundary Layer Flow PDF Download
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Author: F. M. White
Publisher:
ISBN:
Category :
Languages : en
Pages : 114
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Book Description
The report concerns the calculation of coupled skin friction and heat transfer in compressible, turbulent, three-dimensional boundary layers. It presents an integral method of solution which assumes law-of-the-wall velocity and temperature correlations and results in three, coupled partial differential equations whose dependent variables are the dimensionless components of local skin friction and the dimensionless local heat transfer. The method allows for the specification of arbitrary distributions of free stream pressure, Mach number and wall temperature. The present theory is capable of handling problems of extreme complexity with moderate difficulty. (Modified author abstract).
Author: F. M. White
Publisher:
ISBN:
Category :
Languages : en
Pages : 114
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Book Description
The report concerns the calculation of coupled skin friction and heat transfer in compressible, turbulent, three-dimensional boundary layers. It presents an integral method of solution which assumes law-of-the-wall velocity and temperature correlations and results in three, coupled partial differential equations whose dependent variables are the dimensionless components of local skin friction and the dimensionless local heat transfer. The method allows for the specification of arbitrary distributions of free stream pressure, Mach number and wall temperature. The present theory is capable of handling problems of extreme complexity with moderate difficulty. (Modified author abstract).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
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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: Donald M. Wilson
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 82
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Book Description
Turbulent boundary-layer heat transfer and skin-friction coefficients were measured on sharp slender cones at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios from 0.15 to 0.80 were obtained by precooling or preheating the model. Tests were conducted for a wide range of Reynolds numbers by varying the tunnel supply pressure and temperature, thus providing data for naturally turbulent boundary layers. The experimental results were compared with existing theories which predict convective Stanton number or skin-friction coefficients. These comparisons indicate that the heat-transfer data are best predicted by the Spalding-Chi law and the skin friction by the Sommer-Short reference temperature method. The experimental Reynolds analogy factor is adequately predicted by Colburn's incompressible correlation for wall-to-stagnation temperature ratios above about 0.5. However, for lower wall temperature ratios, the experimental Reynolds analogy factor decreases with decreased temperature ratios in a manner which has not been previously reported. (Author).
Author: Neal Tetervin
Publisher:
ISBN:
Category : Enthalpy
Languages : en
Pages : 96
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The method predicts that a positive pressure gradient increases and a negative pressure gradient decreases the ratio of Stanton number to friction coefficient. The Crocco relation between the velocity and total enthalpy for a non-adiabatic surface and zero pressure gradient is generalized to non-zero pressure gradient. The relation between the velocity and the total enthalpy varies markedly from the flat plate Crocco relation as the pressure gradient departs from zero. The magnitude of the variation depends on the velocity profile shape parameter. (Author).
Author: J. Boccio
Publisher:
ISBN:
Category : Equations of motion
Languages : en
Pages : 50
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Book Description
An analysis of the incompressible turbulent boundary layer, developing under the combined effects of mass transfer and pressure gradient, is presented in this paper. A strip-integral method is employed whereby two of the three governing equations are obtained by integrating the combined momentum and continuity equation to 50 percent and 100 percent, respectively, of the boundary-layer height. The latter equation is the usual momentum-integral equation; the former equation requires specification of shear. Accordingly, Clauser's equilibrium eddy-viscosity law is assumed valid at this point. The third and final equation is obtained by specifying that Stevenson's velocity profiles apply throughout the domain of interest, from which a skin-friction law can be derived. Comparisons of the numerical results with the experiments of McQuaid, which include combined effects of variable pressure gradient and mass transfer, show good agreement.
Author: L. J. Johnston
Publisher:
ISBN:
Category : Turbulent boundary layer
Languages : en
Pages : 40
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 620
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 368
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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