Books on the topic 'Supersonic combustion ramjet engines'

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

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.

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.

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

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.

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.

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

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

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.

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

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

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

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.

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

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

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

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

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.

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

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

Center, Langley Research, ed. A two-line absorption instrument for scramjet temperature and water vapor concentration measurement in HYPULSE. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. Neuilly sur Seine, France: AGARD, 1990.

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. Neuilly sur Seine, France: AGARD, 1990.

L, Semenov Vyacheslav, Hicks John W, Hugh L. Dryden Flight Research Center., and United States. National Aeronautics and Space Administration., eds. Recent flight test results of the joint CIAM-NASA Mach 6.5 Scramjet Flight Program. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

L, Semenov Vyacheslav, Hicks John W, and Hugh L. Dryden Flight Research Center., eds. Recent flight test results of the joint CIAM-NASA Mach 6.5 Scramjet Flight Program. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

Center, Langley Research, ed. High-speed engine/component performance assessment using exergy and thrust-based methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

Center, Langley Research, ed. High-speed engine/component performance assessment using exergy and thrust-based methods. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1996.

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.

United States. National Aeronautics and Space Administration., ed. Numerical study of supersonic combustors by multi-block grids with mismatched interfaces. [Washington, DC: National Aeronautics and Space Administration, 1990.

N, Tiwari S., and United States. National Aeronautics and Space Administration., eds. Numerical study of hydrogen-air supersonic combustion by using elliptic and parabolized equations. Norfolk, Va: Dept. of Chemical Sciences, College of Sciences, Old Dominion University, 1986.

N, Tiwari S., and United States. National Aeronautics and Space Administration, eds. Numerical study of hydrogen-air supersonic combustion by using elliptic and parabolized equations. Norfolk, Va: Dept. of Chemical Sciences, College of Sciences, Old Dominion University, 1986.

W, Kniskern Marc, Monta William J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

Huebner, Lawrence D. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. Hampton, Va: Langley Research Center, 1993.

W, Kniskern Marc, Monta William J, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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

Center, Ames Research, ed. Air-breathing aerospace plane development essential: Hypersonic propulsion flight tests. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

Mehta, Unmeel B. Air-breathing aerospace plane development essential: Hypersonic propulsion flight tests. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

A, Mackley Ernest, and Langley Research Center, eds. NASA's hypersonic research engine project: A review. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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.

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