Books on the topic 'Scramjet'

T, Curran E., and Murthy S. N. B, eds. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.

United States. National Aeronautics and Space Administration., ed. A first scramjet study. [Washington, DC: National Aeronautics and Space Administration, 1989.

J, Aslan, and Universities Space Research Association, eds. OVRhyp: Scramjet test aircraft. Houston, Tex: Universities Space Research Association, 1990.

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

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, ed. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

The scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.

J, Bakos Robert, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1991.

G, Morgan R., and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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

R, Casey, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1990.

J, Stalker R., and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1993.

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

J, Stalker R., and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1993.

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

United States. National Aeronautics and Space Administration., ed. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC]: National Aeronautics and Space Administration, 1993.

Sislian, Jean Pascal. Inviscid on-design propulsive characteristics of hypersonic shock-induced combustion ramjets. North York, Ont: Institute for Aerospace Studies, University of Toronto, 1997.

United States. National Aeronautics and Space Administration., ed. An extended supersonic combustion model for the dynamic analysis of hypersonic vehicles. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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

J, Stalker R., Paull Alvord, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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

Morgan, R. G. Shock tunnel studies of scramjet phenomena 1994. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

United States. National Aeronautics and Space Administration., ed. Shock tunnel studies of scramjet phenomena 1994. [Brisbane, Australia]: University of Queensland, 1995.

A, Jacobs Peter, and Langley Research Center, eds. Flow establishment in a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

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

J, Stalker R., Paull A, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1995. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

A, Jacobs Peter, and Langley Research Center, eds. Preliminary calibration of a generic scramjet combustor. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, [1991], 1991.

United States. National Aeronautics and Space Administration., ed. Shock tunnel studies of scramjet phenomena 1994. [Brisbane, Australia]: University of Queensland, 1995.

Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

Center, Langley Research, ed. HYPULSE combustor analysis. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

Baysal, Oktay. Navier-Stokes calculations of scramjet-nozzle-afterbody flowfields. Norfolk, Va: Dept. of Mechanical Engineering & Mechanics, College of Engineering & Technology, Old Dominion University Research Foundation, 1991.

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

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

Baysal, Oktay. Navier-Stokes analysis of cold scramjet-afterbody flows. Norfolk, Va: Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, 1989.

Baysal, Oktay. Navier-Stokes calculations of scramjet-nozzle-afterbody flowfields. Norfolk, Va: Dept. of Mechanical Engineering & Mechanics, College of Engineering & Technology, Old Dominion University Research Foundation, 1991.

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

Baysal, Oktay. Navier-Stokes analysis of cold scramjet-afterbody flows. Norfolk, Va: Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, 1989.

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

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

Parent, Bernard. Computational study of fuel injection in a shcramjet inlet. [Downsview, Ont.]: University of Toronto, Institute for Aerospace Studies, 2002.

Steffen, Christopher J. Fuel injector design optimization for an annular scramjet geometry. [Cleveland, Ohio: NASA Glenn Research Center, 2003.

J, Stalker R., and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena 1993: Supplement 10. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Scotti, Stephen J. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

J, Martin Carl, Lucas Stephen H, and Langley Research Center, eds. Active cooling design for scramjet engines using optimization methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

Baysal, Oktay. Viscous computations of cold air/airflow around scramjet nozzle afterbody. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Computational parametric study of sidewall-compression scramjet inlet performance at mach 10. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Edwards, Thomas A. The effect of exhaust plume/afterbody interaction on installed scramjet performance. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1988.

Baysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va: Langley Research Center, 1991.

United States. National Aeronautics and Space Administration., ed. Shock tunnel studies of scramjet phenomena: Final technical report, NAGW-674. [Washington, DC: National Aeronautics and Space Administration, 1996.

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

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