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  • 1
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    Calculation of three-dimensional compressible laminar and turbulent boundary layers. Calculation of three-dimensional compressible boundary layers on arbitrary wings (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A very general method for calculating compressible three-dimensional laminar and turbulent boundary layers on arbitrary wings is described. The method utilizes a nonorthogonal coordinate system for the boundary-layer calculations and includes a geometry package that represents the wing analytically. In the calculations all the geometric parameters of the coordinate system are accounted for. The Reynolds shear-stress terms are modeled by an eddy-viscosity formulation developed by Cebeci. The governing equations are solved by a very efficient two-point finite-difference method used earlier by Keller and Cebeci for two-dimensional flows and later by Cebeci for three-dimensional flows.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Aerodynamic Analyses Requiring Advanced Computers, Pt. 1; p 41-76
    Format: application/pdf
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  • 2
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    Analysis of iced wings (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A method for computing ice shapes along the leading edge of a wing and a method for predicting its aerodynamic performance degradation due to icing is described. Ice shapes are computed using an extension of the LEWICE code which was developed for airfoils. The aerodynamic properties of the iced wing are determined with an interactive scheme in which the solutions of the inviscid flow equations are obtained from a panel method and the solutions of the viscous flow equations are obtained from an inverse three-dimensional finite-difference boundary-layer method. A new interaction law is used to couple the inviscid and viscous flow solutions. The application of the LEWICE wing code to the calculation of ice shapes on a MS-317 swept wing show good agreement with measurements. The interactive boundary layer method is applied to a tapered iced wing in order to study the effect of icing on the aerodynamic properties of the wing at several angles of attack.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0416
    Format: text
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  • 3
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    Some problems of the calculation of three-dimensional boundary layer flows on general configurations (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An accurate solution of the three-dimensional boundary layer equations over general configurations such as those encountered in aircraft and space shuttle design requires a very efficient, fast, and accurate numerical method with suitable turbulence models for the Reynolds stresses. The efficiency, speed, and accuracy of a three-dimensional numerical method together with the turbulence models for the Reynolds stresses are examined. The numerical method is the implicit two-point finite difference approach (Box Method) developed by Keller and applied to the boundary layer equations by Keller and Cebeci. In addition, a study of some of the problems that may arise in the solution of these equations for three-dimensional boundary layer flows over general configurations.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-2285
    Format: application/pdf
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  • 4
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    Compressible laminar boundary layers with suction on swept and tapered wings (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: In this paper we present a numerical method for solving the compressible laminar boundary-layer equations with suction on swept and tapered wings. The method employs an efficient two-point finite-difference method to solve the governing equations, and a very convenient similarity transformation which removes the wall normal velocity as a boundary condition and places it into the governing equations as a parameter. In this way the awkward nonlinear boundary condition which couples all the variables is avoided. To test and demonstrate the method, we present a sample calculation for a typical laminar-flow-control (LFC) wing.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 14; July 197
    Format: text
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  • 5
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    Disturbance amplification rates (1980)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Program computes incompressible linear stability characteristics for swept and tapered wings. Amplification rates of boundary-layer disturbances also are calculated. Program is useful in designing tapered, laminar-flow control wings incorporating suction to prevent boundary layer separation. Program is written in FORTRAN IV and Assembler for batch execution on CYBER 70-series.
    Keywords: MECHANICS
    Type: LAR-12556 , NASA Tech Briefs (ISSN 0145-319X); 5; 1; P. 76
    Format: text
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  • 6
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    A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The method described utilizes a nonorthogonal coordinate system for boundary-layer calculations. It includes a geometry program that represents the wing analytically, and a velocity program that computes the external velocity components from a given experimental pressure distribution when the external velocity distribution is not computed theoretically. The boundary layer method is general, however, and can also be used for an external velocity distribution computed theoretically. Several test cases were computed by this method and the results were checked with other numerical calculations and with experiments when available. A typical computation time (CPU) on an IBM 370/165 computer for one surface of a wing which roughly consist of 30 spanwise stations and 25 streamwise stations, with 30 points across the boundary layer is less than 30 seconds for an incompressible flow and a little more for a compressible flow.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2777
    Format: application/pdf
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  • 7
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    A Computer Program for Calculating Three-Dimensional Compressible Laminar and Turbulent Boundary Layers on Arbitrary Wings (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program for calculating three dimensional compressible laminar and turbulent boundary layers on arbitrary wings is described and presented. The computer program consists of three separate programs, namely, a geometry program to represent the wing analytically, a velocity program to compute the external velocity components from a given experimental pressure distribution and a finite difference boundary layer method to solve the governing equations for compressible flows. To illustrate the usage of the computer program, three different test cases are presented and the preparation of the input data as well as the computed output data is discussed in some detail.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145194
    Format: application/pdf
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  • 8
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    Analysis of iced wings (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method for computing ice shapes along the leading edge of a wing and a method for predicting its aerodynamic performance degradation due to icing is described. Ice shapes are computed using an extension of the LEWICE code which was developed for airfoils. The aerodynamic properties of the iced wing are determined with an interactive scheme in which the solutions of the inviscid flow equations are obtained from a panel method and the solutions of the viscous flow equations are obtained from an inverse three-dimensional finite-difference boundary-layer method. A new interaction law is used to couple the inviscid and viscous flow solutions. The application of the LEWICE wing code to the calculation of ice shapes on a MS-317 swept wing shows good agreement with measurements. The interactive boundary-layer method is applied to a tapered ice wing in order to study the effect of icing on the aerodynamic properties of the wing at several angles of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TM-105773 , E-7201 , NAS 1.15:105773 , Aerospace Sciences Meeting and Exhibit; Jan 06, 1992 - Jan 09, 1992; Reno, NV; United States
    Format: application/pdf
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