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  • 1
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    Multigrid solution of the Euler equations for aircraft configurations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A multigrid scheme for solving the Euler equations is presented. The method has been successfully applied to two-dimensional airfoil calculations on both O-type and C-type meshes. In three dimensions the scheme has proved equally effective and calclations of flows over wing/body combinations are possible with convergence achieved in less than 100 cycles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0093
    Format: text
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  • 2
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    An interaction algorithm for three-dimensional turbulent subsonic aerodynamic juncture region flow (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: (Previously cited in issue 06, p. 796, Accession no. A82-17782)
    Keywords: AERODYNAMICS
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  • 3
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    An interaction algorithm for prediction of mean and fluctuating velocities in two-dimensional aerodynamic wake flows (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical analysis is presented yielding sets of partial differential equations for determination of turbulent aerodynamic flowfields in the vicinity of an airfoil trailing edge. A four phase interaction algorithm is derived to complete the analysis. Following input, the first computational phase is an elementary viscous corrected two dimensional potential flow solution yielding an estimate of the inviscid-flow induced pressure distribution. Phase C involves solution of the turbulent two dimensional boundary layer equations over the trailing edge, with transition to a two dimensional parabolic Navier-Stokes equation system describing the near-wake merging of the upper and lower surface boundary layers. An iteration provides refinement of the potential flow induced pressure coupling to the viscous flow solutions. The final phase is a complete two dimensional Navier-Stokes analysis of the wake flow in the vicinity of a blunt-bases airfoil. A finite element numerical algorithm is presented which is applicable to solution of all partial differential equation sets of inviscid-viscous aerodynamic interaction algorithm. Numerical results are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3301 , COMCO-80-TR-1.0
    Format: application/pdf
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  • 4
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    Experimental Determination of Generalized Venting Characteristics (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Supersonic wind tunnel tests of orifice venting characteristics and three dimensional flow on flat plates
    Keywords: AERODYNAMICS
    Type: NASA-CR-61241 , TR-792-8-368
    Format: application/pdf
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  • 5
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    Prediction and measurement of turbulent aerodynamic trailing edge flows (1980)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A viscous-inviscid interaction algorithm is developed for prediction of two-dimensional mean and fluctuating velocity distributions in the wake immediately downstream of an airfoil trailing edge. A composite pressure field is defined, and a Poisson equation solved for transverse pressure variations. A parabolized form of the time-averaged steady Navier-Stokes equations are solved in conjunction with a viscous-augmented two-dimensional inviscid potential flow analysis. A tensor constitutive equation is employed to predict Reynolds stress distributions from solutions of a turbulence kinetic energy two equation closure model. Numerical predictions compared favorably with detailed experimental data for mean and fluctuating velocities, and Reynolds shear stress distributions, in the trailing edge region of a NACA 63-012 airfoil.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1395 , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO
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  • 6
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    A viscous-inviscid interaction algorithm for three-dimensional turbulent subsonic aerodynamic juncture region flow (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An order-of magnitude analysis of the subsonic, three-dimensional, steady time-averaged Navier-Stokes equations for semibounded aerodynamic juncture geometries yields the parabolic Navier-Stokes simplification. The numerical solution of the resultant pressure Poisson equation is cast into complementary and particular parts, yielding an iterative interaction algorithm with an exterior three-dimensional potential flow solution. A parabolic transverse momentum equation set is constructed, wherein robust enforcement first-order continuity effects is accomplished using a penalty differential constraint concept within a finite element solution algorithm. A Reynolds stress constitutive equation, with low turbulence Reynolds number wall functions, is employed for closure, using parabolic forms of the two-equation turbulent kinetic energy-dissipation equation system. The algorithm is employed to predict the three-dimensional turbulent flowfield in the juncture region formed by two intersecting parabolic arcs at a free-stream Mach-number of 0.08, and Re/C = 600,000/m.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0100 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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