The integral-rocket, dual-combustion ramjet - A new propulsion concept
Author:
Affiliation:
1. Johns Hopkins University, Laurel, Md.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1979-7044
Reference15 articles.
1. The interaction of shock waves and heat addition in the design of supersonic combustors
2. Structure of Shock Waves in Cylindrical Ducts
3. Prediction of Precombustion Wall Pressure Distributions in Scramjet Engines
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1. SCRAM - A Supersonic Combustion Ramjet Missile;29th Joint Propulsion Conference and Exhibit;1993-06-28
2. Numerical solutions of ramjet nozzle flows;21st Joint Propulsion Conference;1985-07-08
3. Flowfield Analysis of a Scramjet Combustor with a Coaxial Fuel Jet;AIAA Journal;1982-09
4. Scramjet combustor wall boundary layer analysis;17th Joint Propulsion Conference;1981-07-27
5. Aerodynamic and Inlet Flow Characteristics of Several Hypersonic Airbreathing Missile Concepts;Journal of Aircraft;1981-04
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