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  • 1
    Electronic Resource
    Electronic Resource
    Parabolized/Reduced Navier-Stokes Computational Techniques (1992)
    Palo Alto, Calif. : Annual Reviews
    Annual Review of Fluid Mechanics 24 (1992), S. 117-144 
    Details
    ISSN: 0066-4189
    Source: Annual Reviews Electronic Back Volume Collection 1932-2001ff
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1146/annurev.fl.24.010192.001001
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Parabolized/Reduced Navier-Stokes Computational Techniques (1992)
    Annual Reviews
    Details
    Publication Date: 1992-01-01
    Print ISSN: 0066-4189
    Electronic ISSN: 1545-4479
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Annual Reviews
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    PAPER CURRENT
  • 3
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    Simplified curve fits for the thermodynamic properties of equilibrium air (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: New, improved curve fits for the thermodynamic properties of equilibrium air have been developed. The curve fits are for pressure, speed of sound, temperature, entropy, enthalpy, density, and internal energy. These curve fits can be readily incorporated into new or existing computational fluid dynamics codes if real gas effects are desired. The curve fits are constructed from Grabau-type transition functions to model the thermodynamic surfaces in a piecewise manner. The accuracies and continuity of these curve fits are substantially improved over those of previous curve fits. These improvements are due to the incorporation of a small number of additional terms in the approximating polynomials and careful choices of the transition functions. The ranges of validity of the new curve fits are temperatures up to 25 000 K and densities from 10 to the -7 to 10 to the 3d power amagats.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-RP-1181 , L-16276 , NAS 1.61:1181
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Simplified curve fits for the thermodynamic properties of equilibrium air (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: New improved curve fits for the thermodynamic properties of equilibrium air were developed. The curve fits are for p = p(e,rho), a = a(e,rho), T = T(e,rho), s = s(e,rho), T = T(p,rho), h = h(p,rho), rho = rho(p,s), e = e(p,s) and a = a(p,s). These curve fits can be readily incorporated into new or existing Computational Fluid Dynamics (CFD) codes if real-gas effects are desired. The curve fits were constructed using Grabau-type transition functions to model the thermodynamic surfaces in a piecewise manner. The accuracies and continuity of these curve fits are substantially improved over those of previous curve fits appearing in NASA CR-2470. These improvements were due to the incorporation of a small number of additional terms in the approximating polynomials and careful choices of the transition functions. The ranges of validity of the new curve fits are temperatures up to 25,000 K and densities from 10 to the minus 7th to 100 amagats (rho/rho sub 0).
    Keywords: THERMODYNAMICS AND STATISTICAL PHYSICS
    Type: NASA-CR-181245 , NAS 1.26:181245 , ISU-ERI-AMES-86401 , CFD-15
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An upwind algorithm for the parabolized Navier-Stokes equations (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new upwind algorithm based on Roe's scheme has been developed to solve the two-dimensional parabolized Navier-Stokes (PNS) equations. This method does not require the addition of user specified smoothing terms for the capture of discontinuities such as shock waves. Thus, the method is easy to use and can be applied without modification to a wide variety of supersonic flowfields. The advantages and disadvantages of this adaptation are discussed in relation to those of the conventional Beam-Warming scheme in terms of accuracy, stability, computer time and storage, and programming effort. The new algorithm has been validated by applying it to three laminar test cases including flat plate boundary-layer flow, hypersonic flow past a 15 deg compression corner, and hypersonic flow into a converging inlet. The computed results compare well with experiment and show a dramatic improvement in the resolution of flowfield details when compared with the results obtained using the conventional Beam-Warming algorithm.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 86-1117
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Computation of separated flow on a ramp using the space marching conservative supra-characteristics method (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Steady, hypersonic viscous flows over compression corners with streamwise separation have been computed using the space marching Conservative Supra-Characteristics Method (CSCM-S) of Lombard. The CSCM-S method permits stable space marching of the parabolized Navier-Stokes (PNS) equations through large separated flow regions. The present method has been used to compute surface pressure, heat transfer, and skin friction coefficients for two compression corner cases studied experimentally by Holden and Moselle. The computed results compare favorably with previous Navier-Stokes results and the experimental data. The present method has also been compared with the conventional Beam-Warming scheme for solving the PNS equations. Comparison are made for accuracy, computer time, and computer storage.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0564
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Simplified curve fits for the transport properties of equilibrium air (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: New, improved curve fits for the transport properties of equilibruim air have been developed. The curve fits are for viscosity and Prandtl number as functions of temperature and density, and viscosity and thermal conductivity as functions of internal energy and density. The curve fits were constructed using grabau-type transition functions to model the tranport properties of Peng and Pindroh. The resulting curve fits are sufficiently accurate and self-contained so that they can be readily incorporated into new or existing computational fluid dynamics codes. The range of validity of the new curve fits are temperatures up to 15,000 K densities from 10 to the -5 to 10 amagats (rho/rho sub o).
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-178411 , NAS 1.26:178411 , ISU-ERI-AMES-88405
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Numerical computation of viscous flow about unconventional airfoil shapes (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new two-dimensional computer code was developed to analyze the viscous flow around unconventional airfoils at various Mach numbers and angles of attack. The Navier-Stokes equations are solved using an implicit, upwind, finite-volume scheme. Both laminar and turbulent flows can be computed. A new nonequilibrium turbulence closure model was developed for computing 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 code was 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 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 present code in conjunction with the new nonequilibrium turbulence model gives excellent results.
    Keywords: AERODYNAMICS
    Type: NASA-CR-187343 , NAS 1.26:187343 , ISU-ERI-AMES-91-110 , CFD-24
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Application of the implicit MacCormack scheme to the parabolized Navier-Stokes equations (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: MacCormack's implicit finite-difference scheme was used to solve the two-dimensional parabolized Navier-Stokes (PNS) equations. This method for solving the PNS equations does not require the inversion of block tridiagonal systems of algebraic equations and permits the original explicit MacCormack scheme to be employed in those regions where implicit treatment is not needed. The advantages and disadvantages of the present adaptation are discussed in relation to those of the conventional Beam-Warming scheme for a flat plate boundary layer test case. Comparisons are made for accuracy, stability, computer time, computer storage, and ease of implementation. The present method was also applied to a second test case of hypersonic laminar flow over a 15% compression corner. The computed results compare favorably with experiment and a numerical solution of the complete Navier-Stokes equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-166579 , NAS 1.26:166579 , ISU-ERI-AMES-84432
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    NASA TECHNICAL REPORTS
  • 10
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    A new PNS code for three-dimensional chemically reacting 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, viscous, chemically reacting flow fields around three-dimensional bodies. The flow medium is assumed to be a multicomponent mixture of thermally perfect but calorically imperfect gases. The new PNS code solves the gasdynamic and species conservation equations in a coupled manner using a noniterative, implicit, approximately-factored, finite-difference algorithm. The space-marching method is made well-posed by special treatment of the streamwise pressure gradient term. The code has been used to compute hypersonic laminar flow of chemically reacting air over cones at angles of attack. The results of the computations are compared with the results of reacting boundary-layer computations and show excellent agreement.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 87-1472
    Format: text
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    NASA TECHNICAL REPORTS
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