Books on the topic 'Hypersonic boundary layer'

Marvin, J. G. Turbulence modeling for hypersonic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

Goldstein, M. F. Spatial evolution of nonlinear acoustic mode instabilities on hypersonic boundary layers. [Washington, DC]: National Aeronautics and Space Administration, 1990.

Townend, L. H. Intakes and boundary layer crossflows for hypersonic vehicles. New York: American Institute of Aeronautics and Astronautics, 1991.

Wilmoth, Richard G. Interference effects on the hypersonic, rarefied flow about a flat plate. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

Wendt, Volker. Experimentelle Untersuchung der Instabilitat von ebenen und konischen laminaren Hyperschallgrenzschichten. Koln, Germany: DLR, 1993.

Hamed, A. Flow separation in shock wave boundary layer interactions at hypersonic speeds. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Moraes, Augusto C. M. Compressible laminar boundary layers for perfect and real gases in equilibrium at Mach numbers to 30. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

Fu, Yibin B. Crossflow effects on the growth rate of inviscid Gortler vortices in a hypersonic boundary layer. Hampton Va: Institute for Computer Applications in Science and Engineering, 1992.

Lee, Jong-Hun. Hypersonic three-dimensional nonequilibrium boundary-layer equations in generalized curvilinear coordinates. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Lee, Jong-Hun. Hypersonic three-dimensional nonequilibrium boundary-layer equations in generalized curvilinear coordinates. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Lee, Jong-Hun. Hypersonic three-dimensional nonequilibrium boundary-layer equations in generalized curvilinear coordinates. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Coratekin, Turan. Numerical simulation of turbulent shock/boundary-layer interactions in hypersonic flows. Düsseldorf: VDI Verlag, 2000.

Vermeulen, J. P. Parametric studies of shock wave/boundary layer interactions over 2D compression corners at Mach 6. Rhode Saint Genese, Belgium: von Karman Institute for Fluid Dynamics, 1992.

Nagamatsu, Henry T. Computational, theoretical, and experimental investigation of flow over a sharp flat plate, M1 = 10 - 25. Washington, D. C: American Institute of Aeronautics and Astronautics, 1994.

Lin, Zhen Bin. The investigation of the structure of hypersonic turbulent boundary layers on a 5 degree sharp cone using the electron beam fluorescence technique. London: Imperial College of Science and Technology, 1986.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Special course on shock-wave/boundary-layer interactions in supersonic and hypersonic flows. Neuilly-sur-Seine: AGARD, 1993.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Special course on shock wave boundary layer interactions in supersonic and hypersonic flows. Neuilly-sur-Seine, France: AGARD, 1993.

Glass, Christopher E. Aerothermal tests of spherical dome protuberances on a flat plate at a Mach number of 6.5. Hampton, Va: Langley Research Center, 1986.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Special course on three-dimensional supersonic/hypersonic flows including separation. Neuilly-sur-Seine: AGARD, 1990.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Special course on three-dimensional supersonic/hypersonic flows including separation. Neuilly sur Seine, France: AGARD, 1990.

Hawboldt, R. J. Experimental study of shock wave and hypersonic boundary layer interactions near a convex corner. Downsview, Ont: University of Toronto, Institute for Aerospace Studies, 1993.

Fu, Yibin B. Effects of Gortler vortices, wall cooling and gas dissociation on the Rayleigh instability in a hypersonic boundary layer. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

Richards, W. Lance. Finite-element analysis of a Mach-8 flight test article using nonlinear contact elements. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

Wood, William A. Aerothermodynamic calculations on X-34 at Mach 6 wind tunnel conditions. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

Avery, Don E. Experimental aerodynamic heating to simulated space shuttle tiles in laminar and turbulent boundary layers with variable flow angles at a nominal Mach number of 7. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Holland, Scott D. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Bardina, Jorge E. Turbulence modeling ; Turbulence compressibility corrections ; Three-dimensional Navier-Stokes method with two-equation turbulence models for efficient numerical simulation of hypersonic flows ; Three-dimensional Navier-Stokes simulations with two-equation turbulence models of intersecting shock-waves/turbulent boundary layer at Mach 8.3. San Jose, Calif: MCAT Institute, 1995.

1945-, Harloff G. J., and Lewis Research Center, eds. Hypersonic turbulent wall boundary layer computations. Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1988.

J, Dodson Lori, and Ames Research Center, eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

J, Dodson Lori, and United States. National Aeronautics and Space Administration., eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1991.

J, Dodson Lori, and United States. National Aeronautics and Space Administration., eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1991.

J, Dodson Lori, and Ames Research Center, eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

J, Dodson Lori, and United States. National Aeronautics and Space Administration., eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

J, Dodson Lori, and United States. National Aeronautics and Space Administration., eds. Hypersonic shock/boundary-layer interaction database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1991.

Hypersonic turbulent boundary-layer and free shear database. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

Center, Ames Research, ed. Transpiration cooling of hypersonic blunt bodies with finite rate surface reactions. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

Viscous Hypersonic Flow: Theory of Reacting and Hypersonic Boundary Layers. Dover Publications, Incorporated, 2017.

Ruban, Anatoly I. Classical Boundary-Layer Theory. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780199681754.003.0002.

Three-Dimensional Hypersonic Boundary Layer Stability and Transition. Storming Media, 1997.

An engineering method for interactive inviscid-boundary layers. [Washington, DC: National Aeronautics and Space Administration, 1992.

Stephen, Cowley, Hall Philip, and Langley Research Center, eds. On the instability of hypersonic flow past a flat plate. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

United States. National Aeronautics and Space Administration., ed. Experimental studies of hypersonic shock-wave boundary-layer interactions. Arlington, Tex: University of Texas at Arlington, 1992.

A, Bauserman Willard, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Total temperature probes for high-temperature hypersonic boundary-layer measurements. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments. Storming Media, 2000.

A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

Center, Langley Research, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Nonparallel instability of supersonic and hypersonic boundary layers. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

United States. National Aeronautics and Space Administration., ed. Turbulence measurements in hypersonic boundary layers using contant-temperature anemometry and Reynolds stress measurements in hypersonic boundary layers: Final grant report. [Washington, D.C: National Aeronautics and Space Administration, 1995.