Comparison of computational codes for modeling hydrogen-oxygen injectors-Reference-Cited by-同舟云学术

Comparison of computational codes for modeling hydrogen-oxygen injectors

Published:1997-07-06 Issue: Volume: Page:
ISSN:
Container-title:33rd Joint Propulsion Conference and Exhibit
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Author:

Schley Clive-Axel¹,Hagemann Gerald¹,Tucker P.²,Venkateswaran Sankaran³,Merkle Charles³,Schley Clive-Axel¹,Hagemann Gerald¹,Tucker P.²,Venkateswaran Sankaran³,Merkle Charles³

Affiliation:

1. German Aerospace Research Establishment, Lampoldshausen Research Centre, Hardthausen, Germany

2. NASA, Marshall Space Flight Center, Huntsville, AL

3. Pennsylvania State Univ., University Park

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1997-3302

Reference37 articles.

1. Comparison of high pressure H2/O2 rocket model-engine reference simulations

2. Propulsion-related flowfields using the preconditioned Navier-Stokesequations

3. OH-radical imaging and velocity field measurements in a gaseous hydrogen/oxygen rocket

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1. Numerical study of high-pressure GO2/GH2 combustion of a single-element injector;Science China Technological Sciences;2012-07-02

2. Turbulence-Chemistry Interaction and Heat Transfer Modeling of H2/O2 Gaseous Injector Flows;48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition;2010-01-04

3. Computational Assessment of Gaseous Reacting Flows in Single Element Injector;47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition;2009-01-05

4. Computational Modeling and Sensitivity Evaluation of Liquid Rocket Injector Flow;43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit;2007-07-08

5. Three-Dimensional Simulations of a Gas/Gas, Hydrogen/Oxygen Engine;41st Aerospace Sciences Meeting and Exhibit;2003-01-06