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  • 1
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    BLAYER- COMPRESSIBLE LAMINAR AND TURBULENT BOUNDARY LAYERS IN ARBITRARY PRESSURE GRADIENTS (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This program solves the two-dimensional, compressible laminar or turbulent boundary-layer equations in an arbitrary pressure gradient. Cohen and Reshotko's method is used for the laminar boundary layer, Sasman and Cresci's method for the turbulent boundary layer, and the Schlichting-Ulrich-Granville method to predict transition. Transition may also be forced at any point by the user. Separation, if it occurs, is predicted for both laminar and turbulent flow. The user may begin values for displacement thickness and momentum thickness in either laminar or turbulent flow. This program was implemented on the IBM 7094.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: LEW-11097
    Format: text
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  • 2
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    Computational fluid mechanics of internal flow (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-16
    Description: Major solution techniques for internal computational fluid mechanics are discussed and some examples are presented. The major steps involved in developing a large computer code are then discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 187-230
    Format: text
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  • 3
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    Introduction to boundary-layer theory (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The pressure ratio across a turbine provides a certain amount of ideal energy that is available to the turbine for producing work. The portion of the ideal energy that is not converted to work is considered to be a loss. One of the more important and difficult aspects of turbine design is the prediction of the losses. The primary cause of losses is the boundary layer that develops on the blade and end wall surfaces. Boundary-layer theory is used to calculate the parameters needed to estimate viscous (friction) losses.
    Keywords: FLUID MECHANICS
    Type: Turbine Design and Appl., Vol. 2; p 57-92
    Format: text
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  • 4
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    Review - Computational methods for internal flows with emphasis on turbomachinery (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Current computational methods for analyzing flows in turbomachinery and other related internal propulsion components are presented. The methods are divided into two classes. The inviscid methods deal specifically with turbomachinery applications. Viscous methods, deal with generalized duct flows as well as flows in turbomachinery passages. Inviscid methods are categorized into the potential, stream function, and Euler approaches. Viscous methods are treated in terms of parabolic, partially parabolic, and elliptic procedures. Various grids used in association with these procedures are also discussed.
    Keywords: AERODYNAMICS
    Type: ASME, Transactions, Journal of Fluids Engineering (ISSN 0098-2202); 107; 6-22
    Format: text
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  • 5
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    FORTRAN program for computing coordinates of circular-arc, single and tandem, turbine and compressor, blade sections on a plane (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Coordinates for circular arc blade section of aircraft high speed compressor gas turbines were computed using FORTRAN 4 program. Aerodynamic configurations studied include single segment airfoils, airfoils with slots, and mutiple segment tandem arranged airfoil.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-11237
    Format: application/pdf
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  • 6
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    Computer program /TURBLE/ for calculating velocities and streamlines in turbomachines (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Program is used in design of turbomachinery blade rows, where fluid velocities in blade to blade passage must be obtained. TURBLE requires input data on blade geometry, meridional stream-channel geometry, total flow conditions, weight flow, and inlet and outlet flow angles.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-10788
    Format: application/pdf
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  • 7
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    Flow velocities and streamlines (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computer program calculates subsonic or transonic flow on hubshroud, midchannel, stream surface of single-blade row of turbomachine. Program uses finite-different and quasi-orthogonal (velocity-gradient) methods. Program is reported in two volumes: Part I is User's Manual, Part II is Programmer's Manual.
    Keywords: MECHANICS
    Type: LEW-12966 , NASA Tech Briefs (ISSN 0145-319X); 3; 1; P. 100
    Format: text
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  • 8
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    FORTRAN program for generating a two-dimensional orthogonal mesh between two arbitrary boundaries (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer program is described which computes and plots coordinates for two-dimensional orthogonal mesh for channel containing solid body, about which flow passes and which spans channel from one wall to the other.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-11863
    Format: application/pdf
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  • 9
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    Program for calculating laminar and turbulent boundary layers in arbitrary pressure gradients (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer program predicts growth of boundary layers along any surface where air is flowing. Two integral methods, Cohen-Reshotko and Sasman-Cresici, calculate laminar boundary layers and turbulent boundary layers, respectively; Schlichting-Granville method predicts transition from laminar to turbulent flow.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LEW-11097
    Format: application/pdf
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  • 10
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    FORTRAN program for generating a two-dimensional orthogonal mesh between two arbitrary boundaries (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A FORTRAN 4 program is presented which computes and plots coordinates for a two-dimensional orthogonal mesh in the region between the walls of a flow channel. The program is designed for a channel containing a body about which flow passes and which spans the channel from one wall to the other. However, the condition that the channel contain an immersed body can be easily removed from the program. Input to the program consists of spline points of the channel walls and the body geometry. Output includes printed and plotted coordinates of the generated orthogonal mesh and angles of the mesh with the horizontal plane.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6766 , E-6644
    Format: application/pdf
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