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  • 1
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    Calculation of compressible flow about three-dimensional inlets with auxiliary inlets, slats and vanes by means of a panel method (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An efficient and user-oriented method has been constructed for calculating flow in and about complex inlet configurations. Efficiency is attained by: the use of a panel method, a technique of superposition for obtaining solutions at any inlet operating condition, and employment of an advanced matrix-iteration technique for solving large full systems of equations, including the nonlinear equations for the Kutta condition. User concerns are addressed by the provision of several novel graphical output options that, taken together, yield a more complete comprehension of the flowfield than had been possible previously. Examples of these features are presented for some complicated configurations, and where possible, comparisons are made between calculation and experiment.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1196
    Format: text
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  • 2
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    New approach to the solution of large, full matrix equations (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new approach to the solution of matrix equations resulting from integral equations is presented and applied to the solution of two-dimensional Neumann problems describing the inviscid, incompressible flow past an airfoil. The problem is reformulated in terms of a preselected set of mode functions giving an equivalent matrix equation to be solved for the mode-function expansion coefficients. Because of the inherent smoothness of the original problem, the coefficient problem can be solved approximately without significantly affecting the accuracy of the final solution. Very promising two-dimensional results are obtained and the extension of the method to three-dimensional problems is investigated. On the basis of these results it is shown that the computing time for the matrix solution for a large three-dimensional panel method calculation could be reduced by an order of magnitude compared with that required for a direct solution.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Feb. 198
    Format: text
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  • 3
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    Wind tunnel investigation of rotor lift and propulsive force at high speed. Test data appendix (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-10020.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145217-APP-2 , D210-11135-2
    Format: application/pdf
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  • 4
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    Wind tunnel investigation of rotor lift and propulsive force at high speed: Test data appendix (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N78-10020.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145217-APP-3 , D210-11135-3-APP
    Format: application/pdf
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  • 5
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    Wind tunnel investigation of rotor lift and propulsive force at high speed: Data analysis (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The basic test data obtained during the lift-propulsive force limit wind tunnel test conducted on a scale model CH-47b rotor are analyzed. Included are the rotor control positions, blade loads and six components of rotor force and moment, corrected for hub tares. Performance and blade loads are presented as the rotor lift limit is approached at fixed levels of rotor propulsive force coefficients and rotor tip speeds. Performance and blade load trends are documented for fixed levels of rotor lift coefficient as propulsive force is increased to the maximum obtainable by the model rotor. Test data is also included that defines the effect of stall proximity on rotor control power. The basic test data plots are presented in volumes 2 and 3.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145217-APP-1 , D210-11135-1
    Format: application/pdf
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  • 6
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    Calculation of compressible flow about three-dimensional inlets with auxiliary inlets, slats and vanes by means of a panel method (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An efficient and user oriented method was constructed for calculating flow in and about complex inlet configurations. Efficiency is attained by: (1) the use of a panel method; (2) a technique of superposition for obtaining solutions at any inlet operating condition; and (3) employment of an advanced matrix iteration technique for solving large full systems of equations, including the nonlinear equations for the Kutta condition. User concerns are addressed by the provision of several novel graphical output options that yield a more complete comprehension of the flowfield than was possible previously.
    Keywords: AERODYNAMICS
    Type: NASA-CR-174975 , NAS 1.26:174975 , MDC-J3789
    Format: application/pdf
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