Numerical Study of Staged Fuel Injection for Supersonic Combustion
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.51202
Reference7 articles.
1. Initial wind tunnel tests at Mach 4 and 7 of a hydrogen-burning, airframe-integrated scramjet
2. Numerical investigation of the perpendicular injector flow field in a hydrogen fueled scramjet
3. Numerical study of a scramjet engine flow field
4. A numerical method for solving the Navier-Stokes equations with application to shock-boundary layer interactions
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