Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber-Reference-Cited by-同舟云学术

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Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber

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

Author:

Wadel Mary¹,Wadel Mary¹

Affiliation:

1. NASA, Lewis Research Center, Cleveland, OH

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1997-2913

Reference18 articles.

1. Validation of high aspect ratio cooling in a 89 kN (20,000 lbf) thrust combustion chamber

2. Wadel,M.F.,Quentmeyer,R.J.,Meyer,M.L.:ARocket Engine Design for Validating the High Aspect RatioCoolingChannelConcept,NASACP-3282, Vol.H,pp. 145-150.

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