Books on the topic 'Ramjet engines'

Northam, G. Burton. Supersonic combustion ramjet research at Langley. New York: AIAA, 1986.

Kremer, Frans G. J. Thermodynamische Stromungsbeschreibung eines Staustrahltriebwerks mit Unterschallverbrennung zur Bestimmung der Triebwerkskrafte und Momente. Koln: Deutsche Forschungsanstalt fur Luft- und Raumfahrt, 1991.

Snyder, Christopher. A parametric study of a gas-generator airturbo ramjet (ATR). [Washington, DC]: National Aeronautics and Space Administration, 1986.

Snyder, Christopher. The design and performance estimates for the propulsion module for the booster of a TSTO vehicle. [Washington, DC]: National Aeronautics and Space Administration, 1991.

Artëmov, Oleg Aleksandrovič. Prjamotočnye vozdušno-reaktivnye dvigateli: (rasčet charakteristik) : monografija. Moskva: Kompanija Sputnik+, 2006.

Seokkwan, Yoon, and United States. National Aeronautics and Space Administration., eds. Numerical study of chemically reacting flows using an LU scheme. [Washington, DC: National Aeronautics and Space Administration, 1988.

Wittenberg, H. Some fundamentals on the performance of ramjets with subsonic and supersonic combustion. Rijswijk, The Netherlands: TNO Prins Maurits Laboratory, 2000.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Experimental and analytical methods for the determination of connected-pipe ramjet and ducted rocket internal performance. Neuilly sur Seine, France: AGARD, 1994.

Burkardt, Leo A. RAMSCRAM: A flexible ramjet/scramjet engine simulation program. [Washington, DC]: National Aeronautics and Space Administration, 1990.

Dash, Sanford M. Computational models for the analysis/design of hypersonic scramjet nozzles - Part 1: Combustor and nozzle models. New York: AIAA, 1986.

Jacobs, P. A. Preliminary calibration of a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1991.

G, McArdle Jack, and United States. National Aeronautics and Space Administration., eds. Experimental performance of a ventral nozzle with pitch and yaw vectoring capability for SSTOVL aircraft. [Washington, DC]: National Aeronautics and Space Administration, 1993.

G, McArdle Jack, and United States. National Aeronautics and Space Administration., eds. Experimental performance of a ventral nozzle with pitch and yaw vectoring capability for SSTOVL aircraft. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Minucci, Marco A. S. Investigation of a 2-D scramjet inlet, M =8-25 and T =800-4, 100K. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Morgan, R. G. Further shock tunnel studies of scramjet phenomena. St.Lucia, Australia: University of Queensland, 1986.

Chernyshev, S. L. Reaktivnye sopla perspektivnykh grazhdanskikh samoletov: Sbornik stateĭ. Moskva: Izdatelʹskiĭ otdel T︠S︡AGI, 2013.

Brescianini, C. P. An investigation of a wall-injected scramjet using a shock tunnel. Washington: AIAA, 1992.

Thomas, Scott R. Scramjet testing from Mach 4 to 20: Present capability and needs for the nineties. Washington, D. C: American Institute of Aeronautics and Astronautics, 1990.

Rogers, R. Clayton. Scramjet mixing establishment times for a pulse facility. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Eklund, Dean R. A numerical and experimental study of a supersonic combustor employing swept ramp fuel injectors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1994.

Lacroze, Jean. René Leduc, pionnier de la propulsion à réaction. Clichy: Larivière, 2000.

Walton, James T. Aerothermodynamic flow phenomena of the airframe-integrated supersonic combustion ramjet. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

Hitch, B. D. Reduced H2-O2 mechanisms for use in reacting flow simulation. New York: AIAA, 1988.

Rizkalla, Oussama F. Calculated chemical and vibrational nonequilibrium effects in NASP-type nozzles. New York: AIAA, 1988.

Holland, Scott D. Schlieren photographs and internal pressure distributions for three-dimensional sidewall-compression scramjet inlets at a Mach number of 6 in CF4. Hampton, Va: Langley Research Center, 1993.

Drummond, J. Philip. Mixing enhancement of reacting parallel fuel jets in a supersonic combustor. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Menon, S. Shock-wave-induced mixing enhancement in scramjet combustors. Washington, D. C: American Institute of Aeronautics and Astronautics, 1989.

O'Neill, Mary Kae L. Optimized scramjet integration on a waverider. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Schumacher, Jurgen. Effects of incomplete fuel/air mixing on the performance characteristics of hypersonic shock-induced combustion ramjets (shcramjets). [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 1995.

Ryerson Polytechnical Institute. Dept. of Mechanical Engineering. Investigations in the fluid dynamics of scramjet inlets. Toronto: Ryerson Polytechnical Institute ; University of Toronto, 1992.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Modifications to the nozzle test chamber to extend nozzle static-test capability. [Washington, D.C.?]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

Anderson, Griffin Y. An outlook on hypersonic flight. New York: AIAA, 1987.

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.

Kumar, Ajay. A mixing augmentation technique for hypervelocity scramjets. Washington: American Institute of Aeronautics and Astronautics, 1987.

Murman, Earll M. Computational analysis of scramjet dual mode operation: Progress report for NASA grant NAG-1-229 for period May 1, 1984-October 31, 1984. Cambridge, Mass: Dept. of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1985.

Silverstein, Calvin C. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

Nusca, Michael J. Numerical simulation of reacting flow in a thermally choked ram accelerator: Model development and validation. Aberdeen Proving Ground, Md: Ballistic Research Laboratory, 1991.

Ishiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan: National Aerospace Laboratory, 1992.

Skyring, R. Experimental determination of hydrogen-air detonation pressure limit and scramjet application. Washington: American Institute of Aeronautics and Astronautics, 1996.

Zhukov, A. N. Virtualʹnye aviadvigateli: Modifikat︠s︡ii︠a︡ struktur s agregatami diskretnogo deĭstvii︠a︡ i ikh ot︠s︡enki. Moskva: Vychislitelʹnyĭ t︠s︡entr im. A.A. Dorodnit︠s︡ina Rossiĭskoĭ akademii nauk, 2010.

Zhukov, A. N. Virtualʹnye aviadvigateli: Termoėlektrichestvo v proizvodstve reaktivnoĭ sily 1. Moskva: Vychislitelʹnyĭ T︠S︡entr im. A.A. Dorodnit︠s︡yna Rossiĭskoĭ akademii nauk, 2012.

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

Jacobs, P. A. Flow establishment in a generic scramjet combustor. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1990.

Schetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.

Oppitz, Rick. Aerothermodynamic performance of mixed compression, shock-induced combustion ramjets. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 1995.

Schwartzentruber, Thomas. Suppression of premature ignition in the pre-mixed inlet flow of a shcramjet. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2003.

Timnat, Y. M. Advanced airbreathing propulsion. Malabar, Fla: Krieger Pub. Co., 1996.

Waitz, Ian A. An investigation of a contoured wall injector for hypervelocity mixing augmentation. Washington, D. C: American Institute of Aeronautics and Astronautics, 1991.

Bement, David A. Measured operating characteristics of a rectangular combustor/inlet isolator. Washington: American Institute of Aeronautics and Astronautics, 1990.

United States. National Aeronautics and Space Administration., ed. Options for flight testing rocket-based combined-cycle (RBCC) engines. Reston, VA: American Institute of Aeronautics and Astronautics, 1996.