Similar Solutions for Turbulent Boundary Layer with Large Favorble Pressures Gradients (nozzle Flow with Heat Transfer) PDF Download
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Author: James F. Schmidt
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 68
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Book Description
In order to provide a relatively simple heat-transfer prediction along a nozzle, a differential (similar-solution) analysis for the turbulent boundary layer is developed. This analysis along with a new correlation for the turbulent Prandtl number gives good agreement of the predicted with the measured heat transfer in the throat and supersonic regiono f the nozzle. Also, the boundary-layer variables (heat transfer, etc. ) can be calculated at any arbitrary location in the throat or supersonic region of the nozzle in less than a half minute of computing time (Lewis DCS 7094-7044).
Author: James F. Schmidt
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 68
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Book Description
In order to provide a relatively simple heat-transfer prediction along a nozzle, a differential (similar-solution) analysis for the turbulent boundary layer is developed. This analysis along with a new correlation for the turbulent Prandtl number gives good agreement of the predicted with the measured heat transfer in the throat and supersonic regiono f the nozzle. Also, the boundary-layer variables (heat transfer, etc. ) can be calculated at any arbitrary location in the throat or supersonic region of the nozzle in less than a half minute of computing time (Lewis DCS 7094-7044).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 810
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1386
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1508
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Book Description
Author: John C. Adams
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
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Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1408
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 364
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Book Description
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 36
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Book Description
An empirical modification of an existing integral energy turbulent boundary layer method is proposed in order to improve the estimates of local heat transfer in converging-diverging nozzles and consequently, provide better assessments of the total or integrated heat transfer. The method involves the use of a modified momentum-heat analogy which includes an acceleration term comprising the nozzle geometry and free stream velocity. The original and modified theories are applied to heat transfer data from previous studies which used heated air in 30 deg - 15 deg, 45 deg - 15 deg, and 60 deg - 15 deg water-cooled nozzles.
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 628
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Book Description
Author: James F. Schmidt
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 36
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Book Description
A two-dimensional differential analysis is developed to approximate the turbulent boundary layer on a compressor blade element with strong adverse pressure gradients, including the separated region with reverse flow. The predicted turbulent boundary layer thicknesses and velocity profiles are in good agreement with experimental data for a cascade blade, even in the separated region.
