Plasma Actuator–Assisted Rocket Nozzle for Improved Launcher Performance
Author:
Affiliation:
1. Polytechnic University of Turin, 10129 Torino, Italy
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J057956
Reference38 articles.
1. Effects of Limitation of Nozzle Flow Separation on Launcher Performance
2. Sea level side loads in high-area-ratio rocket engines
3. Viscous and Inviscid Vortex Generation During Startup of Rocket Nozzles
4. Side-Load Phenomena in Highly Overexpanded Rocket Nozzles
5. Advanced Rocket Nozzles
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