Feasibility of Aerodynamic-Tab Jet Noise Suppressors in a Hypersonic Nozzle at Takeoff
Author:
Affiliation:
1. Gunma University, 376-8515 Kiryu, Japan
2. Honda R&D Company, Ltd., 351-0024 Asaka, Japan
3. Japan Aerospace Exploration Agency, 182-8522 Tokyo, Japan
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.J051474
Reference12 articles.
1. Firing Test of a Hypersonic Turbojet Engine Installed on a Flight Test Vehicle
2. Design and Fabrication of Variable Nozzle for Precooled Turbojet Engine
3. Shear flow control by mechanical tabs
4. Effect of tabs on the flow and noise field of an axisymmetric jet
5. Spreading characteristics of compressible jets from nozzles of various geometries
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