Books on the topic 'High Knudsen Number Flow'

Lepicovsky, J. Coherent large-scale structures in high Reynolds number supersonic jets. Marietta, Ga: Lockheed-Georgia Company, 1985.

Mavriplis, Dimitri J. Unstructured and adaptive mesh generation for high Reynolds number viscous flows. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

Sandborn, Virgil A. Evaluation of high reynolds number flow in a 180 degree turn-around duct. [Washington, DC: National Aeronautics and Space Administration, 1991.

Stalker, R. J. Thermodynamics and wave processes in high Mach number propulsive ducts. Washington: AIAA, 1989.

Bayliss, Alvin. Wave phenomena in a high Reynolds number compressible boundary layer. Hampton, Va: ICASE, 1985.

Papageorgiou, D. T. The stability of two-dimensional wakes and shear-layers at high Mach numbers. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

Shigemi, Masashi. Finite element analysis of incompressible viscous flows around single and multi-element aerofoils in high Reynolds number region. Tokyo: National Aerospace Laboratory, 1988.

Jacobs, P. A. Simulation of transient flow in a shock tunnel and a high Mach number nozzle. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

Jacobs, Peter A. Simulation of transient flow in a shock tunnel and a high mach number nozzle. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Ishida, Yoji. Numerical and experimental study of drag characteristics of two-dimensional HLFC airfoils in high subsonic, high Reynolds number flow. Chofu, Tokyo: National Aerospace Laboratory, 1994.

Pfenninger, Werner. Optimization of natural laminar flow airfoils for high section lift-to-drag ratios in the lower Reynolds number range. Washington, D. C: AIAA, 1989.

Bonhaus, Daryl L. Assessment of an Euler-interacting boundary layer method using high Reynolds number transonic flight data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Hirose, Naoki. Comparison of transonic airfoil characteristics by Navier-Stokes computation and by wind tunnel test at high Reynolds number. Tokyo: National Aerospace Laboratory, 1986.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

Applin, Zachary T. Wing pressure distributions from subsonic tests of a high-wing transport model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Applin, Zachary T. Wing pressure distributions from subsonic tests of a high-wing transport model. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Yuan, S. P. A near-wall Reynolds-stress closure without wall normals. [Washington, DC: National Aeronautics and Space Administration, 1997.

Chan, Y. Y. Analysis of experimental data for cast 10-2/DOA 2 supercritical airfoil at low Reynolds numbers and application to high Reynolds number flow. Ottawa: National Research Council of Canada, 1989.

Boyle, Robert J. Heat transfer predictions for two turbine nozzle geometries at high Reynolds and Mach numbers. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Boyle, Robert J. Heat transfer predictions for two turbine nozzle geometries at high Reynolds and Mach numbers. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

Fisher, David F. F-18 High Alpha Research Vehicle surface pressures: Initial in-flight results and correlation with flow visualization and wind-tunnel data. Edwards, Calif: NASA Ames Resarch Center, Dryden Flight Research Facility, 1990.

Fisher, David F. F-18 High Alpha Research Vehicle surface pressures: Initial in-flight results and correlation with flow visualization and wind-tunnel data. Edwards, Calif: NASA Ames Resarch Center, Dryden Flight Research Facility, 1990.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1988.

Powers, Sheryll Goecke. Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers. Edwards, Cal: Dryden Flight Research Facility, 1986.

J, Petersen Brian, Scott David D, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. A dynamic response model for pressure sensors in continuum and high Knudsen number flows with large temperature gradients. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

1934-, Jameson Antony, and United States. National Aeronautics and Space Administration, eds. High-resolution shock capturing scheme for high Mach number internal flow. [Washington, D.C.]: National Aeronautics and Space Administration, 1986.

1934-, Jameson Antony, and United States. National Aeronautics and Space Administration, eds. High-resolution shock capturing scheme for high Mach number internal flow. [Washington, D.C.]: National Aeronautics and Space Administration, 1986.

High-resolution shock capturing scheme for high Mach number internal flow. [Washington, D.C.]: National Aeronautics and Space Administration, 1986.

High-resolution shock capturing scheme for high Mach number internal flow. [Washington, D.C.]: National Aeronautics and Space Administration, 1986.

R, Mankbadi R., and United States. National Aeronautics and Space Administration., eds. Numerical simulation of a high mach number jet flow. [Washington, D.C.]: NASA, 1993.

High Reynolds number hybrid laminar flow control (HLFC) flight experiment. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

United States. National Aeronautics and Space Administration., ed. A finite element computational method for high Reynolds number laminar flows. [Washington, DC: National Aeronautics and Space Administration, 1987.

S, Ukeiley Lawrence, Lee Sang W, and Langley Research Center, eds. Aeroacoustic data for a high Reynolds number axisymmetric subsonic jet. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Institute for Computer Applications in Science and Engineering. and United States. National Aeronautics and Space Administration., eds. Directional agglomeration multigrid techniques for high-Reynolds number viscous flows. Hampton, VA: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1998.

Institute for Computer Applications in Science and Engineering., ed. Directional agglomeration multigrid techniques for high-Reynolds number viscous flows. Hampton, VA: Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, 1998.

Zhao, Wancheng. High schmidt number mass transfer at rough surfaces in pipe flow. 1995.

Directional agglomeration multigrid techniques for high Reynolds number viscous flow solvers. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

United States. National Aeronautics and Space Administration., ed. Directional agglomeration multigrid techniques for high Reynolds number viscous flow solvers. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

Institute for Computer Applications in Science and Engineering., ed. The stability of two-dimensional wakes and shear-layers at high Mach numbers. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

Institute for Computer Applications in Science and Engineering., ed. The stability of two-dimensional wakes and shear-layers at high Mach numbers. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

J, Donnelly Russell, and Sreenivasan Katepalli R, eds. Flow at ultra-high Reynolds and Rayleigh numbers: A status report. New York: Springer, 1998.

Shih, T. H. A new k-epsilon eddy viscosity model for high Reynolds number turbulent flow. 1994.

Aerodynamics and heat transfer investigations on a high Reynolds number turbine cascade. [Washington, DC]: NASA, 1991.

Chuen-Yen, Chow, Chang Sin-Chung, and United States. National Aeronautics and Space Administration., eds. High resolution Euler solvers based on the space-time conservation element and solution element method. Washington, D.C: American Institute of Aeronautics and Astronautics, 1996.

The Influence of Surface Roughness on Supersonic High Reynolds Number Turbulent Boundary Layer Flow. Storming Media, 1998.

Experimental Investigation of Vortex Shedding in High Reynolds Number Flow Over Compressor Blades in Cascade. Storming Media, 2003.

Lewis Research Center. Institute for Computational Mechanics in Propulsion., ed. Effects of artificial viscosity on the accuracy of high-Reynolds-number [kappa-epsilon] turbulence model. Cleveland, Ohio: NASA, Lewis Research Center, Institute for Computational Mechanics in Propulsion, 1994.

Experiments on the flow field physics of confluent boundary layers for high-lift systems. [Washington, DC: National Aeronautics and Space Administration, 1994.

V, Maddalon Dal, and Langley Research Center, eds. Assessment of an Euler-interacting boundary layer method using high Reynolds number transonic transport flight data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

V, Maddalon Dal, and Langley Research Center, eds. Assessment of an Euler-interacting boundary layer method using high Reynolds number transonic transport flight data. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.