A Quasi-2-D Model for the Prediction of the Wall Temperature of Rocket Engine Cooling Channels
Author:
Publisher
Informa UK Limited
Subject
Condensed Matter Physics,Numerical Analysis
Link
http://www.tandfonline.com/doi/pdf/10.1080/10407782.2011.578011
Reference38 articles.
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2. M. L. Meyer , Electrically Heated Tube Investigation of Cooling Channel Geometry Effects, AIAA Paper 1995-2500, 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference, San Diego, CA, July 10–12, 1995.
3. M. F. Wadel, Comparison of High Aspect Ratio Cooling Channel Designs for a Rocket Combustion Chamber, AIAA Paper 1997-2913, 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Seattle, WA, July 6–9, 1997.
4. A. Fröhlich , M. Popp , G. Schmidt , and D. Thelemann , Heat Transfer Characteristic of H2/O2– Combustion Chambers, AIAA Paper 1993-1826, 29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Monterey, CA, June 28–30, 1993.
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