Books on the topic 'Nozzle Design'
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Griffith, Wayland C. Hypersonic nozzle design. North Carolina State University, 1989.
Find full textSmith, 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). Lewis Research Center, 1987.
Find full textDudebout, Rudy. Axisymmetric hypersonic contoured nozzle design. National Library of Canada, 1990.
Find full textDudebout, Rudy. Axisymmetric hypersonic contoured nozzle design. Dept. of Aerospace Science and Engineering, 1989.
Find full textKacynski, Kenneth J. Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle. Lewis Research Center, 1987.
Find full textGoing, M. Nozzle design optimization by method-of-characteristics. American Institute of Aeronautics and Astronautics, 1990.
Find full textScallion, W. I. Effects of nozzle exit geometry and pressure ratio on plume shape for nozzles exhausting into quiescent air. National Aeronautics and Space Administration, Langley Research Center, 1991.
Find full textScallion, W. I. Effects of nozzle exit geometry and pressure ratio on plume shape for nozzles exhausting into quiescent air. National Aeronautics and Space Administration, Langley Research Center, 1991.
Find full textHussaini, M. Moin. Investigation of low-Reynolds-number rocket nozzle design using PNS-based optimization procedure. National Aeronautics and Space Administration, Langley Research Center, 1996.
Find full textRuffin, Stephen M. Computational design aspects of a NASP nozzle/afterbody experiment. American Institute of Aeronautics and Astronautics, 1989.
Find full textHannemann, Klaus. Design of an axisymmetric, contoured nozzle for the HEG. Deutsche Forschungsanstalt fur Luft- und Raumfahrt, 1990.
Find full textDash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. AIAA, 1986.
Find full textLeavitt, Laurence D. Static internal performance of a single-engine nonaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilities. NASA, 1985.
Find full textHarloff, G. J. Two-dimensional viscous flow computations of hypersonic scramjet nozzle flowfields at design and off design conditions. National Aeronautics and Space Administration, 1988.
Find full textHarloff, G. J. Two-dimensional viscous flow computations of hypersonic scramjet nozzle flowfields at design and off design conditions. National Aeronautics and Space Administration, 1988.
Find full textSchneider, Steven P. Development of quiet-flow supersonic wind tunnels for laminar-turbulent transition research: Final report. National Aeronautics and Space Administration, 1994.
Find full textMarable, R. W. Design, fabrication, and test of the RL10 derivative II chamber/primary nozzle. Pratt and Whitney Aircraft, 1989.
Find full textBaysal, Oktay. Flow analysis and design optimization methods for nozzle afterbody of a hypersonic vehicle. Langley Research Center, 1992.
Find full textBaysal, Oktay. Flow analysis and design optimization methods for nozzle after body of a hypersonic vehicle. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.
Find full textBrown, W. H. Enhancement of mixing in a rectangular jet by mechanical tabs. National Aeronautics and Space Administration, 1990.
Find full textGeorge, Russell J. Flight motor set 360L001 (STS-26R): Final report. Thiokol Corp., Space Operations, 1989.
Find full textGeorge, Russell J. Flight motor set 360L001 (STS-26R): Final report. Thiokol Corp., Space Operations, 1989.
Find full textSchneider, Steven P. Method of characteristics design of a supersonic wind tunnel nozzle with square cross-section: Status report for NASA Langley grant NAG-1-113, supplement 3. National Aeronautics and Space Administration, 1993.
Find full textAbdol-Hamid, Khaled S. Development of three-dimensional code for the analysis of jet mixing problem. For sale by the National Technical Information Service, 1988.
Find full textBarna, P. S. Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel: Progress report on the D.S.M.A. design. National Aeronautics and Space Administration, Langley Research Center, 1995.
Find full textSimeonides, G. The aerodynamic design of hypersonic contoured axisymmetric nozzles including real gas effects. von Karman Institute for Fluid Dynamics, 1987.
Find full textWatmuff, J. H. Design of a new contraction for the ARL low speed wind tunnel (U). Aeronautical Research Laboratories, 1986.
Find full textFietz, T. R. An aid to the design of orifice plates according to ISO code 5167. University of New South Wales, Water Research Laboratory, 1988.
Find full textNozue, Sonoko. Japanese beadwork with Sonoko Nozue: 25 jewelry designs from a master artist. Lark Crafts, 2012.
Find full textJ, Sovie Amy, Haag Thomas W, and United States. National Aeronautics and Space Administration., eds. Arcjet nozzle design impacts. National Aeronautics and Space Administration, 1989.
Find full textHypersonic nozzle design: Final report. National Aeronautics and Space Administration, Langley Research Center, 1990.
Find full textG, Keith Theo, and United States. National Aeronautics and Space Administration., eds. Analysis and design of optimized truncated scarfed nozzles subject to external flow effects. National Aeronautics and Space Administration, 1990.
Find full textMultidisciplinary approach to aerospike nozzle design. National Aeronautics and Space Administration, Langley Research Center, 1997.
Find full textCenter, NASA Glenn Research, ed. First NASA/Industry High Speed Research Program Nozzle Symposium. National Aeronautics and Space Administration, Glenn Research Center, 1999.
Find full textCenter, NASA Glenn Research, ed. First NASA/Industry High Speed Research Program Nozzle Symposium. National Aeronautics and Space Administration, Glenn Research Center, 1999.
Find full textREMTECH SSME nozzle design TPS: Final report. National Aeronautics and Space Administration, 1990.
Find full textUse of the PARC code to estimate the off-design transonic performance of an over/under turboramjet nozzle. National Aeronautics and Space Administration, 1995.
Find full textUnited States. National Aeronautics and Space Administration., ed. NPAC--nozzle performance analysis code. National Aeronautics and Space Administration, 1997.
Find full textInvestigation of low-Reynolds-number rocket nozzle design using PNS-based optimization procedure. National Aeronautics and Space Administration, Langley Research Center, 1996.
Find full textInvestigation of low-Reynolds-number rocket nozzle design using PNS-based optimization procedure. National Aeronautics and Space Administration, Langley Research Center, 1996.
Find full textCenter, NASA Glenn Research, ed. Decomposing solid micropropulsion nozzle performance issues. National Aeronautics and Space Administration, Glenn Research Center, 2003.
Find full textM, Gilinsky M., and United States. National Aeronautics and Space Administration., eds. Nozzle thrust optimization while reducing jet noise. National Aeronautics and Space Administration, 1995.
Find full textM, Gilinsky M., and United States. National Aeronautics and Space Administration., eds. Nozzle thrust optimization while reducing jet noise. National Aeronautics and Space Administration, 1995.
Find full textH, Pulliam Thomas, and Research Institute for Advanced Computer Science (U.S.), eds. Aerodynamic design optimization via reduced Hessian SQP with solution refining. Research Institute for Advanced Computer Science, NASA Ames Research Center, 1995.
Find full textH, Pulliam Thomas, and Research Institute for Advanced Computer Science (U.S.), eds. Aerodynamic design optimization via reduced Hessian SQP with solution refining. Research Institute for Advanced Computer Science, NASA Ames Research Center, 1995.
Find full textH, Pulliam Thomas, and Research Institute for Advanced Computer Science (U.S.), eds. Aerodynamic design optimization via reduced Hessian SQP with solution refining. Research Institute for Advanced Computer Science, NASA Ames Research Center, 1995.
Find full textCenter, Langley Research, ed. An approximate theoretical method for modeling the static thrust performance of non-axisymmetric two-dimensional convergent-divergent nozzles. National Aeronautics and Space Administration, Langley Research Center, 1995.
Find full textCenter, Lewis Research, and Pratt & Whitney Aircraft Group. Government Products Division., eds. Convoluted nozzle design for the RL10 derivative IIB engine: Final report. National Aeronautics and Space Administration, Lewis Research Center, 1985.
Find full textD, Wolter John, and Lewis Research Center, eds. Design and checkout of a high speed research nozzle evaluation rig. National Aeronautics and Space Administration, Lewis Research Center, 1997.
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