Livros sobre o tema "Compression flows"

H, Anderson Bernhard, Shaw Robert J. 1946- e United States. National Aeronautics and Space Administration., eds. Numerical simulation of supersonic compression corners and hypersonic inlet flows using the RPLUS2D code. [Washington, DC]: National Aeronautics and Space Administration, 1994.

Center, Ames Research, ed. Steady secondary flows generated by periodic compression and expansion of an ideal gas in a pulse tube. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1999.

B, Roebuck, e National Physical Laboratory (Great Britain), eds. Measuring flow stress in hot axisymmetric compression tests. Teddington: NPL, 1997.

Neuhoff, F. Modifications to the inlet flow field of a transonic compressor rotor. Monterey, Calif: Naval Postgraduate School, 1985.

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

1936-, Kawamura Takaichi, Bencze Daniel P e Ames Research Center, eds. Calculation of external-internal flow fields for mixed-compression inlets. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.

1936-, Kawamura Takaichi, Bencze Daniel P e Ames Research Center, eds. Calculation of external-internal flow fields for mixed-compression inlets. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.

Center, Ames Research, ed. Computations of unsteady multistage compressor flows in a workstation environment. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.

S, Prahst P., e United States. National Aeronautics and Space Administration., eds. Inlet flow test calibration for a small axial compressor facility. [Washington, DC]: National Aeronautics and Space Administration, 1994.

United States. National Aeronautics and Space Administration., ed. Blockage development in a transonic, axial compressor rotor. [Washington, D.C: National Aeronautics and Space Administration, 1997.

United States. National Aeronautics and Space Administration., ed. Blockage development in a transonic, axial compressor rotor. [Washington, D.C: National Aeronautics and Space Administration, 1997.

Ng, Y. K. Eddie. Compressor instability with integral methods. Berlin: Springer, 2007.

Maurice, M. S. The LV measured turbulent structure of Mach 6 flow over a roughened flat plate with a compression ramp. New York: AIAA, 1989.

C, Bidek Maleina, e United States. National Aeronautics and Space Administration., eds. Turbulence models and Reynolds analogy for two-dimensional supersonic compression ramp flow. [Washington, DC: National Aeronautics and Space Administration, 1994.

1939-, Okiishi T. H., e United States. National Aeronautics and Space Administration., eds. Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance. [Washington, DC]: National Aeronautics and Space Administration, 1996.

Cherrett, M. A. Unsteady viscous flow in a high speed core compressor. Farnborough, Hampshire: Procurement Executive, Ministry of Defence, 1990.

Li, Ruiyu, Limin Gao e Lei Zhao. Detached-Eddy Simulation Series Methods for Compressor Internal Flow. Singapore: Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-0255-1.

McKenzie, A. B. Axial compressor development at Rolls-Royce Derby, 1946-1962. Derby: Rolls-Royce Heritage Trust, 2009.

Center, NASA Glenn Research, ed. On hammershock propagation in a supersonic flow field. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

S, Prahst P., e United States. National Aeronautics and Space Administration., eds. Inlet flow test calibration for a small axial compressor rig. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Perttula, Juha. Physical simulation of hot working: Measurements of flow stress and recrystallization kinetics. Oulu: Oulun yliopisto, 1998.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

D, Saunders J., e United States. National Aeronautics and Space Administration., eds. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration., ed. A final report on NASA grant NGL-22-009-383 entitled Unsteady design-point flow phenomena in transonic compressors: Final report. Cambridge, MA: Gas Turbine Laboratory, Dept. of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1986.

Haynes, Joel M. Active control of rotating stall in a three-stage axial compressor. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993.

Hathaway, Michael D. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.

Center, NASA Glenn Research, ed. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.

Center, NASA Glenn Research, ed. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.

Center, NASA Glenn Research, ed. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.

United States. National Aeronautics and Space Administration., ed. Users manual for updated computer code for axial-flow compressor conceptual design. [Washington, DC: National Aeronautics and Space Administration, 1992.

F, Weaver Harold, Senyitko Richard G e United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.

F, Weaver Harold, Senyitko Richard G e United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. NASA low-speed axial compressor for fundamental research. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.

F, Weaver Harold, Senyitko Richard G e United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.

Wasserbauer, Charles A. NASA low-speed axial compressor for fundamental research. Cleveland, Ohio: Lewis Research Center, 1995.

F, Weaver Harold, Senyitko Richard G e United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.

L, Gundy-Burlet Karen, e Ames Research Center, eds. Temporally and spatially resolved flow in a two-stage axial compressor. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

L, Gundy-Burlet Karen, e Ames Research Center, eds. Temporally and spatially resolved flow in a two-stage axial compressor. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

W, Tam C. K., e United States. National Aeronautics and Space Administration., eds. Numerical simulation of the generation of axisymmetric mode jet screech tones. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

W, Tam C. K., e United States. National Aeronautics and Space Administration., eds. Numerical simulation of the generation of axisymmetric mode jet screech tones. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

Moore, John. A prediction of 3-D viscous flow and performance of the NASA low-speed centrifugal compressor. Blacksburg, Va: Mechanical Engineering Dept., Virginia Polytechnic Institute and State University, 1989.

Moore, John. A prediction of 3-D viscous flow and performance of the NASA low-speed centrifugal compressor. Blacksburg, Va: Mechanical Engineering Dept., Virginia Polytechnic Institute and State University, 1989.

C, Smith Steven. Airflow calibration of a bellmouth inlet for measurement of compressor airflow in turbine-powered propulsion simulators. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1985.

Cuellar, Alvaro F. Measurement of synchronous forces and flow non-uniformity in an axial compressor. Monterey, Calif: Naval Postgraduate School, 1997.

United States. National Aeronautics and Space Administration., ed. Experimental determination of aerodynamic damping in a three-syage transonic axial-flow compressor. [Washington, DC: National Aeronautics and Space Administration, 1988.

Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Chung-hua, Wu. A general theory of two-and three-dimensional rotational flow in subsonic and transonic turbomachines. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.