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  • 1
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    Aerodynamic loads near cranks, apexes, and tips of thin, lifting wings in incompressible flow (1977)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The calculation of the incompressible and irrotational flow in the vicinity of tips and corners of thin, lifting wings is considered. It is shown that the important characteristics of the flow are governed by an eigenvalue problem, which is nonlinear at the trailing edge because of the shed wake (assumed to be in the wing plane). A new solution method was devised because either the existing methods were not valid for the trailing edge case or they would have required excessive amounts of computer time. The new method, which is fundamentally different than the previous ones, was used to calculate solutions for a number of cases, including some for which correct answers had not previously been obtained. Two of these solutions were used to determine the validity of drag and leading-edge-suction distributions near the tips of a delta wing and a swept wing as calculated by using both the vortex lattice method and a kernel function method. The calculations for the swept wing resolved the question of whether or not the induced drag should be zero at the wing tip.
    Keywords: AERODYNAMICS
    Type: AGARD Prediction of Aerodynamic Loading; 12 p
    Format: text
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  • 2
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    Plotting program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and users manual for a USA FORTRAN IV computer program which plots the planform and control points of a wing are presented. The program also plots some of the configuration data such as the aspect ratio. The planform data is stored on a disc file which is created by a geometry program. This program, the geometry program, and several other programs are used together in the analysis of lifting, thin wings in steady, subsonic flow according to a kernel function lifting surface theory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62321
    Format: application/pdf
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  • 3
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    Geometry program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program that provides the geometry and boundary conditions appropriate for an analysis of a lifting, thin wing with control surfaces in linearized, subsonic, steady flow is presented. The kernel function method lifting surface theory is applied. The data which is generated by the program is stored on disk files or tapes for later use by programs which calculate an influence matrix, plot the wing planform, and evaluate the loads on the wing. In addition to processing data for subsequent use in a lifting surface analysis, the program is useful for computing area and mean geometric chords of the wing and control surfaces.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62309
    Format: application/pdf
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  • 4
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    Normal loads program for aerodynamic lifting surface theory (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and users manual are presented for a U.S.A. FORTRAN 4 computer program which evaluates spanwise and chordwise loading distributions, lift coefficient, pitching moment coefficient, and other stability derivatives for thin wings in linearized, steady, subsonic flow. The program is based on a kernel function method lifting surface theory and is applicable to a large class of planforms including asymmetrical ones and ones with mixed straight and curved edges.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62326
    Format: application/pdf
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  • 5
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    Influence matrix program for aerodynamic lifting surface theory (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A users manual is described for a USA FORTRAN 4 computer program which computes an aerodynamic influence matrix and is one of several computer programs used to analyze lifting, thin wings in steady, subsonic flow according to a kernel function method lifting surface theory. The most significant features of the program are that it can treat unsymmetrical wings, control points can be placed on the leading and/or trailing edges, and a stable, efficient algorithm is used to compute the influence matrix.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62324
    Format: application/pdf
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  • 6
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    Equation solving program for aerodynamic lifting surface theory (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A description of and user's manual are presented for one of a group of FORTRAN programs which, together, can be used for the analysis and design of wings in steady, subsonic flow according to a kernel function method lifting surface theory. This particular program is the one which solves the sets of simultaneous, linear, algebraic equations arising from the thin wing analysis. This program has the capability of striking out rows and columns of the aerodynamic influence matrix and rows of the associated boundary condition vectors (right hand sides). This capability significantly enhances the effectiveness of the kernel function method of lifting surface theory because studies of the convergence of solutions with the number of control points can be done with the calculation of only a single influence matrix.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62325
    Format: application/pdf
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  • 7
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    Steady, subsonic, lifting surface theory for wings with swept, partial span, trailing edge control surfaces (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for computing the lifting pressure distribution on a wing with partial span, swept control surfaces is presented. This method is valid within the framework of linearized, steady, potential flow theory and consists of using conventional lifting surface theory in conjuction with a flap pressure mode. The cause of a numerical instability that can occur during the quadrature of the flap pressure mode is discussed, and an efficient technique to eliminate the instability is derived. This technique is valid for both the flap pressure mode and regular pressure modes and could be used to improve existing lifting surface methods. Examples of the use of the flap pressure mode and comparisons among this method, other theoretical methods, and experiments are given. Discrepancies with experiment are indicated and candidate causes are presented. It is concluded that the method can lead to an efficient and accurate solution of the mathematical problem when a partial span, trailing edge flap is involved.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7251 , A-4521
    Format: application/pdf
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  • 8
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    NASA-Ames three-dimensional potential flow analysis system (POTFAN) equation solver code (SOLN) version 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program known as SOLN was developed as an independent segment of the NASA-Ames three-dimensional potential flow analysis systems of linear algebraic equations. Methods used include: LU decomposition, Householder's method, a partitioning scheme, and a block successive relaxation method. Due to the independent modular nature of the program, it may be used by itself and not necessarily in conjunction with other segments of the POTFAN system.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-X-73074 , A-6338
    Format: application/pdf
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  • 9
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    Vortex Effects for Canard-wing Configurations at High Angles of Attack in Subsonic Flow (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fully three-dimensional subsonic panel method that can handle arbitrary shed vortex wakes is used to compute the nonlinear forces and moments on simple canard-wing configurations. The lifting surfaces and wakes are represented by doublet panels. The Mangler-Smith theory is used to provide an initial estimate for the vortex sheet shed from the leading edge. The trailing-edge wake and the leading-edge wake downstream of the trailing edge are assumed to be straight and leave the trailing edge at an angle of alpha/2. Results indicate good agreement with experimental data up to 40 degs angle of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78543 , A-7677
    Format: application/pdf
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  • 10
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    Improvements to the kernel function method of steady, subsonic lifting surface theory (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The application of a kernel function lifting surface method to three dimensional, thin wing theory is discussed. A technique for determining the influence functions is presented. The technique is shown to require fewer quadrature points, while still calculating the influence functions accurately enough to guarantee convergence with an increasing number of spanwise quadrature points. The method also treats control points on the wing leading and trailing edges. The report introduces and employs an aspect of the kernel function method which apparently has never been used before and which significantly enhances the efficiency of the kernel function approach.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62327
    Format: application/pdf
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