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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ISBN:
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:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 376
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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: J. Schneider
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Category : Boundary layer
Languages : en
Pages : 106
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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 : Government publications
Languages : en
Pages : 1932
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Author: United States. Superintendent of Documents
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Category : United States
Languages : en
Pages : 1466
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Author:
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Category : Aerodynamic load
Languages : en
Pages : 1092
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The results of the Task 1 and 2 turbine design work are reported. Preliminary design is discussed. Blading detailed design data are summarized. Predicted performance maps are presented. Steady-state stresses and vibratory behavior are discussed, and the results of the mechanical design analysis are presented. -- [V]. I The experimental test program results of a 4 1/2-stage turbine with a very high stage loading factor are presented. A four-stage turbine was tested with and without outlet turning vanes. The 4 1/2-stage turbine achieved a design point total-to-total efficiency of 0.853. The outlet turning vane design point performance was 0.4 percent of the overall 4 1/2-stage turbine efficiency. Tests were conducted at various levels of Reynolds number and indicated decreases in turbine efficiency and equivalent weight flow with decreasing Reynolds number. --[V]. II.
Author:
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ISBN:
Category :
Languages : en
Pages : 100
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Author:
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Category : Aeronautics
Languages : en
Pages : 1270
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Author: C. Economos
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ISBN:
Category : Transformations (Mathematics)
Languages : en
Pages : 92
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A generalized form of the Coles compressibility transformation is utilized to analyze compressible turbulent boundary-layer flows. The generalization in the transformation is distinguished by specifying a stretching parameter that depends upon both space variables rather than on only the streamwise coordinate. This modification is shown to eliminate the distortion observed in the wake region of the transformed velocity profiles. For zero pressure gradient flows, predictions based upon the analysis are consistently superior with predictions due to Spalding-Chi and Baronti-Libby. A wide range of experimental data have been examined with Mach numbers ranging as high as 8, wall to free stream total temperature ratios as low as 0.25 and momentum thickness Reynolds numbers up to approximately one million.
Author: United States. National Technical Information Service
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ISBN:
Category : Computer programs
Languages : en
Pages : 336
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