Inlet Geometry and Equivalence Ratio Effects on Combustion in a Ducted Rocket
Author:
Affiliation:
1. Faculty of Aerospace Engineering, Technion–Israel Institute of Technology, 32000 Haifa, Israel
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B35369
Reference36 articles.
1. A Century of Ramjet Propulsion Technology Evolution
2. Propellant design relationships for throttled gas generators
3. Fit for Mission-Design Tailoring Aspects of Throttleable Ducted Rocket Propulsion Systems
4. Full-Scale Firing Tests of Variable Flow Ducted Rocket Engines Employing Gap Solid Fuel Gas Generator
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