Scramjet Operability Range Studies of a Multifuel Integrated Aeroramp Injector/Plasma Igniter-Reference-Cited by-同舟云学术

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Scramjet Operability Range Studies of a Multifuel Integrated Aeroramp Injector/Plasma Igniter

Published:2005-05-16 Issue: Volume: Page:
ISSN:
Container-title:AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference
language:
Short-container-title:

Author:

Bonanos Aristides¹,Schetz Joseph¹,O'Brien Walter¹,Goyne Christopher²

Affiliation:

1. Virginia Polytechnic Institute and State University

2. University of Virginia

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2005-3425

Reference34 articles.

1. Mixing-Controlled Supersonic Combustion

2. Ignition and Combustion Performance of Scramjet Combustors with Fuel Injection Struts

3. Doerner S.E., Cutler A.D. "Effects of Jet Swirl on Mixing of a Light Gas Jet in a Supersonic Airstream", NASA/CR1999-209842, December1999

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1. Combustion characteristics of a dual-mode ramjet engine with a supersonic aerodynamic ramp injector;Experimental Thermal and Fluid Science;2024-01

2. Combustion;Airbreathing Hypersonic Propulsion;2023

3. Review of combustion stabilization for hypersonic airbreathing propulsion;Progress in Aerospace Sciences;2020-11

4. Reacting flow analysis of a cavity-based scramjet combustor using a Jacobian-free Newton–Krylov method;The Aeronautical Journal;2018-12

5. Effects of Fuel Injectors and Cavity Configurations on Supersonic Combustion;Journal of Propulsion and Power;2013-09

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