Books on the topic 'Nozzles'

Hamed, A. High speed nozzles task: Final report. [Cincinnati, Ohio?]: University of Cincinnati, 1995.

Smith, Tamara A. Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m(2) (350 psia). Cleveland, Ohio: Lewis Research Center, 1987.

G, Keith Theo, and United States. National Aeronautics and Space Administration., eds. Analysis and design of optimized truncated scarfed nozzles subject to external flow effects. [Washington, D.C.]: National Aeronautics and Space Administration, 1990.

Milton, Lamb, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

H, Dieck Ronald, Chuang Isaac, and United States. National Aeronautics and Space Administration., eds. A detailed description of the uncertainty analysis for high area ratio rocket nozzle tests at the NASA Lewis Research Center. [Washington, D.C.?]: National Aeronautics and Space Administration, 1987.

Kacynski, Kenneth J. Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle. Cleveland, Ohio: Lewis Research Center, 1987.

M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

M, Kazaroff John, Pavli Albert J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, eds. Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

Carlson, John R. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton, Va: Langley Research Center, 1994.

Carlson, John R. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton, Va: Langley Research Center, 1994.

C, Asbury Scott, and Langley Research Center, eds. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Carlson, John R. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton: National Aeronautics and Space Administration, Langley Research Center, 1994.

C, Asbury Scott, and Langley Research Center, eds. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

C, Asbury Scott, and Langley Research Center, eds. Two-dimensional converging-diverging rippled nozzles at transonic speeds. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Simakov, Nikolay N. Liquid Spray from Nozzles. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-12446-5.

Pirumov, Ul’yan G., and Gennadi S. Roslyakov. Gas Flow in Nozzles. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-86790-3.

Stepanovich, Rosli͡akov Gennadiĭ, ed. Gas flow in nozzles. Berlin: Springer-Verlag, 1986.

United States. National Aeronautics and Space Administration., ed. Altitude testing of the 2D V/STOL ADEN demonstrator on an F404 engine: Final report. [Cincinnati, OH]: General Electric Company, 1990.

Center, Langley Research, ed. Static performance investigation of a skewed-throat multiaxis thrust-vectoring nozzle concept. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

Landry, John Gary. Nozzle flow with vibrational nonequilibrium. [Washington, DC: National Aeronautics and Space Administration, 1995.

Landry, John Gary. Nozzle flow with vibrational nonequilibrium. [Washington, DC: National Aeronautics and Space Administration, 1995.

Harloff, G. J. Viscous three-dimensional analyses for nozzles for hypersonic propulsion. Cleveland, Ohio: Sverdrup Technology, Inc., NASA Lewis Research Center Group, 1990.

Harloff, G. J. Viscous three-dimensional analyses for nozzles for hypersonic propulsion. Cleveland, Ohio: Sverdrup Technology, Inc., NASA Lewis Research Center Group, 1990.

Scallion, W. I. Effects of nozzle exit geometry and pressure ratio on plume shape for nozzles exhausting into quiescent air. Hamtpon, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Scallion, W. I. Effects of nozzle exit geometry and pressure ratio on plume shape for nozzles exhausting into quiescent air. Hamtpon, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Center, NASA Glenn Research, ed. First NASA/Industry High Speed Research Program Nozzle Symposium. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Center, NASA Glenn Research, ed. First NASA/Industry High Speed Research Program Nozzle Symposium. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

M, Seiner John, Brown Martha C, and Langley Research Center, eds. Near field pressure fluctuations in the exit plane of a choked axisymmetric nozzle. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

J, Capone Francis, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Performance characteristics of two multiaxis thrust-vectoring nozzles at Mach numbers up to 1.28. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

J, Capone Francis, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Performance characteristics of two multiaxis thrust-vectoring nozzles at Mach numbers up to 1.28. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Simeonides, G. The aerodynamic design of hypersonic contoured axisymmetric nozzles including real gas effects. Rhode Saint Genese, Belgium: von Karman Institute for Fluid Dynamics, 1987.

L, Del Roso Richard, Rosario Rubén del, and United States. National Aeronautics and Space Administration., eds. Advanced nozzle and engine components test facility. [Washington, DC]: National Aeronautics and Space Administration, 1992.

United States. National Aeronautics and Space Administration., ed. Comparison of UNL laser imaging and sizing system and a phase/doppler system for analyzing sprays from a NASA nozzle. [Washington, DC: National Aeronautics and Space Administration, 1988.

Bare, E. Ann. Static internal performance of convergent single-expansion-ramp nozzles with various combinations of internal geometric parameters. Hampton, Va: Langley Research Center, 1989.

R, Hingst Warren, and United States. National Aeronautics and Space Administration., eds. Progress toward synergistic hypermixing nozzles. [Washington, DC]: National Aeronautics and Space Administration, 1991.

Davis, D. O. Progress toward synergistic hypermixing nozzles. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Asbury, Scott C. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. Hampton, Va: Langley Research Center, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Ganesh, Raman, and United States. National Aeronautics and Space Administration., eds. Supersonic jets from bevelled rectangular nozzles. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Glahn, U. Von. Two-dimensional nozzle plume characteristics. [Washington, DC: National Aeronautics and Space Administration, 1987.

Capone, Francis J. Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

McArdle, Jack G. Internal reversing flow in a tailpipe offtake configuration for SSTOVL aircraft. [Washington, DC]: National Aeronautics and Space Administration, 1992.

Dudebout, Rudy. Axisymmetric hypersonic contoured nozzle design. [Downsview, Ont.]: Dept. of Aerospace Science and Engineering, 1989.

F, Brausch J., Majjigi R. K, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Free jet feasibility study of a thermal acoustic shield concept for AST/VCE application: Dual stream nozzles. [Washington, D.C.?]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Raman, Ganesh. The flip-flop nozzle extended to supersonic flows. [Washington, DC]: National Aeronautics and Space Administration, 1992.

E, Reubush David, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Static internal performance of a two-dimensional convergent-divergent nozzle with thrust vectoring. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

Murthy, S. N. B. Analysis of supersonic plug nozzle flowfield and heat transfer. [Washington, DC]: National Aeronautics and Space Administration, 1989.