Calculation of Turbulent Boundary Layers with Heat Transfer and Pressure Gradient Utilizing a Compressibility Transformation. Part 3: Computer Program Manual PDF Download
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Author:
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Category :
Languages : en
Pages : 110
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Author:
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ISBN:
Category :
Languages : en
Pages : 110
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Author: Ralph Alois Seban
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ISBN:
Category : Boundary layer
Languages : en
Pages : 194
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Author: J. Schneider
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Category : Boundary layer
Languages : en
Pages : 106
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Book Description
A computer program is described capable of determining the properties of a compressible turbulent boundary layer with pressure gradient and heat transfer. The program treats the two-dimensional problem assuming perfect gas and Crocco integral energy solution. A compressibility transformation is applied to the equation for the conservation of mass and momentum, which relates this flow to a low speed constant property flow with simultaneous mass transfer and pressure gradient. The resulting system of describing equations consists of eight ordinary differential equations which are solved numerically. For Part 1, see N72-12226; for Part 2, see N72-15264.
Author:
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Category : Aeronautics
Languages : en
Pages : 1572
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Author:
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Category : Aerodynamics
Languages : en
Pages : 758
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Author: C. Frederick Hansen
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Category : Air
Languages : en
Pages : 724
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Book Description
The thermodynamic and transport prorerties of high-temperature air are found in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, the specific heats, the speed of sound, the coefficients of viscosity and of thermal conductivity, and the Prandtl numbers for air are tabulated from 500 degrees to 15,000 degrees K over a range of pressure from 0.0001 to 100 atmospheres. The enthalpy of air and the mol fractions of the major components of air can easily be found from the tabulated values for compressibility and energy. It is predicted that the Prandtl number for fully ionized air will become small compared to unity, the order of 0.01, and this implies that boundary layers in such flow will be very transparent to heat flux.
Author: United States. Superintendent of Documents
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ISBN:
Category : United States
Languages : en
Pages : 1408
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Author: Gordon C. Oates
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Category : Aerothermodynamics
Languages : en
Pages : 830
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Author:
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Category : Mechanics, Applied
Languages : en
Pages : 628
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Author: United States. National Advisory Committee for Aeronautics
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
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