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  • 1
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    Numerical simulation of unsteady flow in a hypersonic shock tunnel facility (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the computational work performed on the simulation of a 16-in shock-tunnel facility. The numerical problems encountered during the computation of these flows are discussed along with the validity of some approximations used, notably concerning the reduction of the problem into problems of smaller dimensionality. Quasi-1D simulations can be used to help design experiments, or to better understanding the characteristics of the facility. An application to the design of a nonintrusive diagnostic is shown. The multidimensional flow transients computed include the shock reflection at the end of the driven tube, the shock propagation down the nozzle, and the breaking of the main diaphragm.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-4029
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    An upwind parabolized Navier-Stokes code for chemically reacting flows (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new upwind, parabolized Navier-Stokes (PNS) code has been developed to compute the hypersonic, viscous, chemically reacting flow around two-dimensional or axisymmetric bodies. The new code is an extension of the upwind (perfect gas) PNS code of Lawrence et al. (1986). The upwind algorithm is based on Roe's flux-difference splitting scheme which has been modified to account for real gas effects. The algorithm solves the gas dynamic and species continuity equations in a 'loosely' coupled manner. The new code has been validated by computing the laminar flow (at free stream Mach number 25) of chemically reacting air over a wedge and a cone. The results of these computations are compared with the results from a centrally-differenced, fully coupled, nonequilibrium PNS code. The agreement is excellent, except in the vicinity of the shock wave where the present code exhibits superior shock capturing capabilities.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2614
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    AFE base flow computations (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Hypersonic wake flows behind the Aeroassist Flight Experiment (AFE) geometry are analyzed using two Navier-Stokes flow solvers. Many of the AFE wake features observed in ballistic-range shadowgraphs are simulated using a simple, two-dimensional semicylinder geometry at moderate angles of attack. At free-stream conditions corresponding to a Hypersonic Free Flight Facility (HFFF) AFE experiment, the three-dimensional base flow for the AFE geometry is computed using an ideal-gas, Navier-Stokes solver. The computed results agree reasonably well with the shadowgraphs taken at the HFFF. An ideal-gas and a nonequilibrium Navier-Stokes solver have been coupled and applied to the complete flow around the AFE vehicle at the free-stream conditions corresponding to a nomial trajectory point. Limitations of the coupled ideal-gas and nonequilibrium solution are discussed. The nonequilibrium base flow solution is analyzed for the wake radiation and the radiation profiles along various lines of sight are compared. Finally, the wake unsteadiness is predicted using experimental correlations and the numerical solutions. An adaptive grid code, SAGE, has been used in all the simulations to enhance the solution accuracy. The grid adaptation is found to be necessary in obtaining base flow solutions with accurate flow features.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1372
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Shock Wave Interactions: A CFD Study of CUBRC LENS-II Turbulent Experiments (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results of flow simulations of turbulent shock wave boundary layer interaction experiments performed in the LENS-II tunnel at CUBRC.
    Keywords: Physics (General); Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN15585 , AIAA Aviation and Aeronautics Forum and Exposition; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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  • 5
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    Upwind parabolized Navier-Stokes code for chemically reacting flows (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 4; 149-156
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Shock Wave Interactions: A CFD Study of CUBRC LENS-XX Laminar Experiments (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results from computations of several cases from a blind study conducted by CUBRC in their LENS-XX high enthalpy expansion tunnel facility.
    Keywords: Physics (General); Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN15584 , AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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