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  • 1
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    A three-dimensional incompressible Navier-Stokes flow solver using primitive variables (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 390-396
    Format: text
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  • 2
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    TRANDESNF: A computer program for transonic airfoil design and analysis in nonuniform flow (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The use of a transonic airfoil code for analysis, inverse design, and direct optimization of an airfoil immersed in propfan slipstream is described. A summary of the theoretical method, program capabilities, input format, output variables, and program execution are described. Input data of sample test cases and the corresponding output are given.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4044 , NAS 1.26:4044 , KU-FRL-602-1
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  • 3
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    Transonic airfoil analysis and design in nonuniform flow (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A nonuniform transonic airfoil code is developed for applications in analysis, inverse design and direct optimization involving an airfoil immersed in propfan slipstream. Problems concerning the numerical stability, convergence, divergence and solution oscillations are discussed. The code is validated by comparing with some known results in incompressible flow. A parametric investigation indicates that the airfoil lift-drag ratio can be increased by decreasing the thickness ratio. A better performance can be achieved if the airfoil is located below the slipstream center. Airfoil characteristics designed by the inverse method and a direct optimization are compared. The airfoil designed with the method of direct optimization exhibits better characteristics and achieves a gain of 22 percent in lift-drag ratio with a reduction of 4 percent in thickness.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3991 , NAS 1.26:3991 , CRINC-FRL-602-2
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  • 4
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    An incompressible Navier-Stokes flow solver in three-dimensional curvilinear coordinate systems using primitive variables (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An implicit, finite-difference computer code has been developed to solve the incompressible Navier-Stokes equations in a three-dimensional, curvilinear coordinate system. The pressure-field solution is based on the pseudo compressibility approach in which the time derivative pressure term is introduced into the mass conservation equation to form a set of hyperbolic equations. The solution procedure employs an implicit, approximate factorization scheme. The Reynolds stresses, that are uncoupled from the implicit scheme, are lagged by one time-step to facilitate implementing various levels of the turbulence model. Test problems for external and internal flows are computed, and the results are compared with existing experimental data. The application of this technique for general three-dimensional problems is then demonstrated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0253
    Format: text
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  • 5
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    A solution procedure for three-dimensional incompressible Navier-Stokes equation and its application (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An implicit, finite-difference procedure is presented for numerically solving viscous incompressible flows. For convenience of applying the present method to three-dimensional problems, primitive variables, namely the pressure and velocities, are used. One of the major difficulties in solving incompressible flows that use primitive variables is caused by the pressure field solution method which is used as a mapping procedure to obtain a divergence-free velocity field. The present method is designed to accelerate the pressure-field solution procedure. This is achieved by the method of pseudocompressibility in which the time derivative pressure term is introduced into the mass conservation equation. The pressure wave propagation and the spreading of the viscous effect is investigated using simple test problems. The present study clarifies physical and numerical characteristics of the pseudo-compressible approach in simulating incompressible flows. Computed results for external and internal flows are presented to verify the present procedure. The present algorithm has been shown to be very robust and accurate if the selection of the pseudo-compressibility parameter has been made according to the guidelines given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85978 , A-9801 , NAS 1.15:85978
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  • 6
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    A computational method for viscous incompressible flows (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An implicit, finite-difference procedure for numerically solving viscous incompressible flows is presented. The pressure-field solution is based on the pseudocompressibility method in which a time-derivative pressure term is introduced into the mass-conservation equation to form a set of hyperbolic equations. The pressure-wave propagation and the spreading of the viscous effect is investigated using simple test problems. Computed results for external and internal flows are presented to verify the present method which has proved to be very robust in simulating incompressible flows.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85958 , A-9748 , NAS 1.15:85958
    Format: application/pdf
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  • 7
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    Calculation of vortex lift effect for cambered wings by the suction analogy (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An improved version of Woodward's chord plane aerodynamic panel method for subsonic and supersonic flow is developed for cambered wings exhibiting edge separated vortex flow, including those with leading edge vortex flaps. The exact relation between leading edge thrust and suction force in potential flow is derived. Instead of assuming the rotated suction force to be normal to wing surface at the leading edge, new orientation for the rotated suction force is determined through consideration of the momentum principle. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semi-empirical method. Comparisons of predicted results with available data in subsonic and supersonic flow are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3449 , CRINC/FRL-426-1
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  • 8
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    VORCAM: A computer program for calculating vortex lift effect of cambered wings by the suction analogy (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A user's guide to an improved version of Woodward's chord plane aerodynamic panel computer code is presumed. The guide can be applied to cambered wings exhibiting edge separated flow, including those with leading edge vortex flow at subsonic and supersonic speeds. New orientations for the rotated suction force are employed based on the momentum principal. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semiempirical method.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165800 , NAS 1.26:165800 , CRINC-FRL-426-2
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  • 9
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    On the method of pseudo compressibility for numerically solving incompressible flows (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Pseudo compressibility is used for numerically solving incompressible flows to achieve computational efficiency. The use of pseudo compressibility results in a system of hyperbolic-type equations of motion that introduce waves of finite speed. The interactions of the wave propagation and the vorticity spreading are analyzed. A criterion governing the dependence of the pseudo compressiblity on the Reynolds number and the characteristic length of the flow geometry is obtained that allows for a proper convergence. It is demonstrated that the solution does tend to the incompressible limit. External and internal viscous flow test problems are presented to verify the theory.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0252
    Format: text
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  • 10
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    ATIC Experiment: Preliminary Results from the Flight in 2002 (2003)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Abstract The Advanced Thin Ionization Calorimeter (ATIC) had successful Long Duration Balloon flights from McMurdo, Antarctica in both 2000 and 2002. The instrument consists of a Silicon matrix for charge measurement, a flared graphite target to induce nuclear interactions, scintillator strip hodoscopes for triggering and helping reconstruct trajectory, and a BGO calorimeter to measure the energy of incident particles. In this paper, we discuss the second flight, which lasted 20 days, starting on 12/29/02. Preliminary results from the on-going analysis of the data including the proton and helium spectra are reported.
    Keywords: Instrumentation and Photography
    Type: 28th International Cosmic Ray Conference; Jul 31, 2003 - Aug 07, 2003; Tsukuba; Japan
    Format: text
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