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  • 11
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    A new PNS code for chemical nonequilibrium flows (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new parabolized Navier-Stokes (PNS) code has been developed to compute the hypersonic laminar flow of a multicomponent, chemically reacting mixture of thermally perfect gases over two-dimensional and axisymmetric bodies. The new PNS code solves the gas dynamic and species conservation equations in a coupled manner using a noniterative, implicit, space-marching finite-difference method. The conditions for well-posedness of the space-marching method have been derived from an eigenvalue analysis of the governing equations. The code has been used to compute hypersonic laminar flow of chemically reacting air over wedges and cones. The results of these computations are in good agreement with the results of reacting boundary-layer calculations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0284
    Format: text
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  • 12
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    Numerical solution of Space Shuttle Orbiter flow field including real gas effects (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The hypersonic, laminar flow around the Space Shuttle Orbiter has been computed for both an ideal gas (gamma = 1.2) and equilibrium air using a real-gas, parabolized Navier-Stokes code. This code employs a generalized coordinate transformation; hence, it places no restrictions on the orientation of the solution surfaces. The initial solution in the nose region was computed using a 3-D, real-gas, time-dependent Navier-Stokes code. The thermodynamic and transport properties of equilibrium air were obtained from either approximate curve fits or a table look-up procedure. Numerical results are presented for flight conditions corresponding to the STS-3 trajectory. The computed surface pressures and convective heating rates are compared with data from the STS-3 flight.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1747
    Format: text
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  • 13
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    Application of the implicit MacCormack scheme to the parabolized Navier-Stokes equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1755-176
    Format: text
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  • 14
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    Development of equilibrium air computer programs suitable for numerical computation using time-dependent or shock-capturing methods (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer programs were developed which compute the thermodynamic properties of equilibrium air for use in either the time-dependent or shock-capturing computational methods. For the time-dependent method, tne NASA-ARC RGAS computer program was modified to allow internal energy and density to be used as the independent variables. In addition, simplified-curve fits for p = p(e,rho), a = a(e,rho), and T = T(p,rho) were devised to reduce computer time. For the shock-capturing method a simplified curve fit for h = h(p,rho) was made. These approximate curve fits may be particularly useful when employed on advanced computers such as the Illiac 4 or the CDC Star since they avoid the cumbersome table-lookup feature of the RGAS program.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-2134
    Format: application/pdf
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  • 15
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    On improving the iterative convergence properties of an implicit approximate-factorization finite difference algorithm (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The iterative convergence properties of an approximate-factorization implicit finite-difference algorithm are analyzed both theoretically and numerically. Modifications to the base algorithm were made to remove the inconsistency in the original implementation of artificial dissipation. In this way, the steady-state solution became independent of the time-step, and much larger time-steps can be used stably. To accelerate the iterative convergence, large time-steps and a cyclic sequence of time-steps were used. For a model transonic flow problem governed by the Euler equations, convergence was achieved with 10 times fewer time-steps using the modified differencing scheme. A particular form of instability due to variable coefficients is also analyzed.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TM-78495 , A-7474
    Format: application/pdf
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  • 16
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    Numerical prediction of turbulent flow over airfoil sections with a new nonequilibrium turbulence model (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new nonequilibrium turbulence closure model has been developed for computing wall bounded two-dimensional turbulent flows. This two-layer eddy viscosity model was motivated by the success of the Johnson-King model in separated flow regions. The influence of history effects are described by an ordinary differential equation developed from the turbulent kinetic energy equation. The performance of the present model has been evaluated by solving the flow around three airfoils using the Reynolds time-averaged Navier-Stokes equations. Excellent results were obtained for both attached and separated turbulent flows about the NACA 0012 airfoil, the RAE 2822 airfoil, and the Integrated Technology A 153W airfoil. Based on the comparison of the numerical solutions with the available experimental data, it is concluded that the new nonequilibrium turbulence model accurately captures the history effects of convection and diffusion on turbulence.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-1469
    Format: text
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  • 17
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    Numerical computation of three-dimensional blunt body flow fields with an impinging shock (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A time-marching finite-difference method was used to solve the compressible Navier-Stokes equations for the three-dimensional wing-leading-edge shock impingement problem. The bow shock was treated as a discontinuity across which the exact shock jump conditions were applied. All interior shock layer detail such as shear layers, shock waves, jets, and the wall boundary layer were automatically captured in the solution. The impinging shock was introduced by discontinuously changing the freestream conditions across the intersection line at the bow shock. A special storage-saving procedure for sweeping through the finite-difference mesh was developed which reduces the required amount of computer storage by at least a factor of two without sacrificing the execution time. Numerical results are presented for infinite cylinder blunt body cases as well as the three-dimensional shock impingement case. The numerical results are compared with existing experimental and theoretical results.
    Keywords: AERODYNAMICS
    Type: NASA-CR-143312 , ISU-ERI-AMES-75169
    Format: application/pdf
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  • 18
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    Improved curve fits for the thermodynamic properties of equilibrium air suitable for numerical computation using time-dependent or shock-capturing methods, part 1 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simplified curve fits for the thermodynamic properties of equilibrium air were devised for use in either the time-dependent or shock-capturing computational methods. For the time-dependent method, curve fits were developed for p = p(e, rho), a = a(e, rho), and T = T(e, rho). For the shock-capturing method, curve fits were developed for h = h(p, rho) and T = T(p, rho). The ranges of validity for these curves fits were for temperatures up to 25,000 K and densities from 10 to the minus 7th power to 10 to the 3d power amagats. These approximate curve fits are considered particularly useful when employed on advanced computers such as the Burroughs ILLIAC 4 or the CDC STAR.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-2470
    Format: application/pdf
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  • 19
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    Numerical Simulation of Supersonic MHD Flows using an Iterative PNS Algorithm (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This final report summarizes the research accomplished under NASA-Ames Cooperative Agreement NCC2-5517 during the period which extended from August 1, 2002 to July 31,2004.
    Keywords: Aerodynamics
    Format: application/pdf
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  • 20
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    Parabolized Navier-Stokes Code for Computing Magneto-Hydrodynamic Flowfields (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This report consists of two published papers, 'Computation of Magnetohydrodynamic Flows Using an Iterative PNS Algorithm' and 'Numerical Simulation of Turbulent MHD Flows Using an Iterative PNS Algorithm'.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: application/pdf
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