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  • AERODYNAMICS  (6)
  • 1975-1979  (6)
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  • 1
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    Prospects for computational aerodynamics (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The integral representations approach, for the solution of the Navier-Stokes equations is discussed as well as experience in its development and in applying available finite-difference and finite-element techniques to the treatment of three-dimensional problems, and the computation of turbulent flow. The magnitude of efforts required to develop turbulence models and three-dimensional algorithms indicates that the computational fluid dynamics research must have a broad base. Broader access to modern computing facilities that are in existence within NASA should be promoted for active researchers not directly affiliated with that agency.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics; p 221-227
    Format: text
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  • 2
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    Considerations of some critical ejector problems (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some aspects of ejector design and application, including, three dimensional effects and cross flow effects are presented.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Workshop on Thrust Augmenting Ejectors; p 363-384
    Format: application/pdf
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  • 3
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    Study of viscous flow about airfoils by the integro-differential method (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An integro-differential method was used for numerically solving unsteady incompressible viscous flow problems. A computer program was prepared to solve the problem of an impulsively started 9% thick symmetric Joukowski airfoil at an angle of attack of 15 deg and a Reynolds number of 1000. Some of the results obtained for this problem were discussed and compared with related work completed previously. Two numerical procedures were used, an Alternating Direction Implicit (ADI) method and a Successive Line Relaxation (SLR) method. Generally, the ADI solution agrees well with the SLR solution and with previous results are stations away from the trailing edge. At the trailing edge station, the ADI solution differs substantially from previous results, while the vorticity profiles obtained from the SLR method there are in good qualitative agreement with previous results.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145693
    Format: application/pdf
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  • 4
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    Optimum performance and potential flow field of hovering rotors (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Rotor and propeller performance and induced potential flowfields were studied on the basis of a rotating actuator disk concept, with special emphasis on rotors hovering out of ground effect. A new theory for the optimum performance of rotors hovering OGE is developed and presented. An extended theory for the optimum performance of rotors and propellers in axial motion is also presented. Numerical results are presented for the optimum distributions of blade-bound circulation together with axial inflow and ultimate wake velocities for the hovering rotor over the range of thrust coefficient of interest in rotorcraft applications. Shapes of the stream tubes and of the velocities in the slipstream are obtained, using available methods, for optimum and off-optimum circulation distributions for rotors hovering in and out of ground effect. A number of explicit formulae useful in computing rotor and propeller induced flows are presented for stream functions and velocities due to distributions of circular vortices over axi-symmetric surfaces.
    Keywords: AERODYNAMICS
    Type: NASA-CR-137705
    Format: application/pdf
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  • 5
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    A numerical study of viscous flow around an airfoil (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An integrodifferential method, previously formulated in terms of velocity and vorticity vectors, is reformulated in terms of stream function and vorticity for two-dimensional incompressible viscous flows. The reformulated integrodifferential method is shown to retain the distinguishing feature of the previous formulation in permitting the confinement of the solution field to the viscous region of the flow and consequently offers great computational advantages. The application of this procedure in a study of an incompressible flow around an impulsively started 9% thick symmetric Joukowski airfoil at an angle of attack of 15 deg and a Reynolds number of 1000 is discussed. Numerical results are presented and compared with available finite-difference results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-337 , Fluid and Plasma Dynamics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
    Format: text
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  • 6
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    Numeric calculation of unsteady forces over thin pointed wings in sonic flow (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A fast and reasonably accurate numerical procedure is proposed for the solution of a simplified unsteady transonic equation. The approach described takes into account many of the effects of the steady flow field. The resulting accuracy is within a few per cent and can be carried out on a computer in less than one minute per case (one frequency and one mode of oscillation). The problem concerns a rigid pointed wing which performs harmonic pitching oscillations of small amplitude in a steady uniform transonic flow. Wake influence is ignored and shocks must be weak. It is shown that the method is more flexible than the transonic box method proposed by Rodemich and Andrew (1965) in that it can easily account for variable local Mach number and rather arbitrary planform so long as the basic assumptions are fulfilled.
    Keywords: AERODYNAMICS
    Type: Unsteady aerodynamics; Mar 18, 1975 - Mar 20, 1975; Tucson, AZ
    Format: text
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