Bücher zum Thema „Compression flows“
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H, Anderson Bernhard, Shaw Robert J. 1946- und United States. National Aeronautics and Space Administration., Hrsg. Numerical simulation of supersonic compression corners and hypersonic inlet flows using the RPLUS2D code. [Washington, DC]: National Aeronautics and Space Administration, 1994.
Den vollen Inhalt der Quelle findenCenter, Ames Research, Hrsg. 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.
Den vollen Inhalt der Quelle findenB, Roebuck, und National Physical Laboratory (Great Britain), Hrsg. Measuring flow stress in hot axisymmetric compression tests. Teddington: NPL, 1997.
Den vollen Inhalt der Quelle findenNeuhoff, F. Modifications to the inlet flow field of a transonic compressor rotor. Monterey, Calif: Naval Postgraduate School, 1985.
Den vollen Inhalt der Quelle findenStalker, R. J. Thermodynamics and wave processes in high Mach number propulsive ducts. Washington: AIAA, 1989.
Den vollen Inhalt der Quelle finden1936-, Kawamura Takaichi, Bencze Daniel P und Ames Research Center, Hrsg. Calculation of external-internal flow fields for mixed-compression inlets. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.
Den vollen Inhalt der Quelle finden1936-, Kawamura Takaichi, Bencze Daniel P und Ames Research Center, Hrsg. Calculation of external-internal flow fields for mixed-compression inlets. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1987.
Den vollen Inhalt der Quelle findenCenter, Ames Research, Hrsg. Computations of unsteady multistage compressor flows in a workstation environment. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1992.
Den vollen Inhalt der Quelle findenS, Prahst P., und United States. National Aeronautics and Space Administration., Hrsg. Inlet flow test calibration for a small axial compressor facility. [Washington, DC]: National Aeronautics and Space Administration, 1994.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration., Hrsg. Blockage development in a transonic, axial compressor rotor. [Washington, D.C: National Aeronautics and Space Administration, 1997.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration., Hrsg. Blockage development in a transonic, axial compressor rotor. [Washington, D.C: National Aeronautics and Space Administration, 1997.
Den vollen Inhalt der Quelle findenNg, Y. K. Eddie. Compressor instability with integral methods. Berlin: Springer, 2007.
Den vollen Inhalt der Quelle findenMaurice, M. S. The LV measured turbulent structure of Mach 6 flow over a roughened flat plate with a compression ramp. New York: AIAA, 1989.
Den vollen Inhalt der Quelle findenC, Bidek Maleina, und United States. National Aeronautics and Space Administration., Hrsg. Turbulence models and Reynolds analogy for two-dimensional supersonic compression ramp flow. [Washington, DC: National Aeronautics and Space Administration, 1994.
Den vollen Inhalt der Quelle finden1939-, Okiishi T. H., und United States. National Aeronautics and Space Administration., Hrsg. Effects of shrouded stator cavity flows on multistage axial compressor aerodynamic performance. [Washington, DC]: National Aeronautics and Space Administration, 1996.
Den vollen Inhalt der Quelle findenCherrett, M. A. Unsteady viscous flow in a high speed core compressor. Farnborough, Hampshire: Procurement Executive, Ministry of Defence, 1990.
Den vollen Inhalt der Quelle findenLi, Ruiyu, Limin Gao und 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.
Der volle Inhalt der QuelleMcKenzie, A. B. Axial compressor development at Rolls-Royce Derby, 1946-1962. Derby: Rolls-Royce Heritage Trust, 2009.
Den vollen Inhalt der Quelle findenCenter, NASA Glenn Research, Hrsg. On hammershock propagation in a supersonic flow field. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. 3D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenS, Prahst P., und United States. National Aeronautics and Space Administration., Hrsg. Inlet flow test calibration for a small axial compressor rig. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenPerttula, Juha. Physical simulation of hot working: Measurements of flow stress and recrystallization kinetics. Oulu: Oulun yliopisto, 1998.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenD, Saunders J., und United States. National Aeronautics and Space Administration., Hrsg. Parametrics on 2D Navier-Stokes analysis of a Mach 2.68 bifurcated rectangular mixed-compression inlet. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration., Hrsg. 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.
Den vollen Inhalt der Quelle findenHaynes, Joel M. Active control of rotating stall in a three-stage axial compressor. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993.
Den vollen Inhalt der Quelle findenHathaway, Michael D. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Den vollen Inhalt der Quelle findenCenter, NASA Glenn Research, Hrsg. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Den vollen Inhalt der Quelle findenCenter, NASA Glenn Research, Hrsg. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Den vollen Inhalt der Quelle findenCenter, NASA Glenn Research, Hrsg. Self-recirculating casing treatment concept for enhanced compressor performance. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration., Hrsg. Users manual for updated computer code for axial-flow compressor conceptual design. [Washington, DC: National Aeronautics and Space Administration, 1992.
Den vollen Inhalt der Quelle findenF, Weaver Harold, Senyitko Richard G und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.
Den vollen Inhalt der Quelle findenF, Weaver Harold, Senyitko Richard G und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. 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.
Den vollen Inhalt der Quelle findenF, Weaver Harold, Senyitko Richard G und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.
Den vollen Inhalt der Quelle findenWasserbauer, Charles A. NASA low-speed axial compressor for fundamental research. Cleveland, Ohio: Lewis Research Center, 1995.
Den vollen Inhalt der Quelle findenF, Weaver Harold, Senyitko Richard G und United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., Hrsg. NASA low-speed axial compressor for fundamental research. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1995.
Den vollen Inhalt der Quelle findenL, Gundy-Burlet Karen, und Ames Research Center, Hrsg. Temporally and spatially resolved flow in a two-stage axial compressor. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.
Den vollen Inhalt der Quelle findenL, Gundy-Burlet Karen, und Ames Research Center, Hrsg. Temporally and spatially resolved flow in a two-stage axial compressor. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.
Den vollen Inhalt der Quelle findenW, Tam C. K., und United States. National Aeronautics and Space Administration., Hrsg. Numerical simulation of the generation of axisymmetric mode jet screech tones. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.
Den vollen Inhalt der Quelle findenW, Tam C. K., und United States. National Aeronautics and Space Administration., Hrsg. Numerical simulation of the generation of axisymmetric mode jet screech tones. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.
Den vollen Inhalt der Quelle findenMoore, 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.
Den vollen Inhalt der Quelle findenMoore, 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.
Den vollen Inhalt der Quelle findenC, 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.
Den vollen Inhalt der Quelle findenCuellar, Alvaro F. Measurement of synchronous forces and flow non-uniformity in an axial compressor. Monterey, Calif: Naval Postgraduate School, 1997.
Den vollen Inhalt der Quelle findenUnited States. National Aeronautics and Space Administration., Hrsg. Experimental determination of aerodynamic damping in a three-syage transonic axial-flow compressor. [Washington, DC: National Aeronautics and Space Administration, 1988.
Den vollen Inhalt der Quelle findenChung-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.
Den vollen Inhalt der Quelle findenChung-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.
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