Validation of high aspect ratio cooling in a 89 kN (20,000 lbf) thrust combustion chamber-Reference-Cited by-同舟云学术

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

Published:1996-07-01 Issue: Volume: Page:
ISSN:
Container-title:32nd Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Wadel Mary¹,Meyer Michael¹

Affiliation:

1. NASA, Lewis Research Center, Cleveland, OH

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1996-2584

Reference18 articles.

1. Naraghi,M.H.N.:User'sManual,RTE-A ComputerCodeforThree-Dimensional Rocket ThermalEvaluation, Manhattan College, Riverdale,NY,September 1993,underNASA grant NAG3-892.

2. Nickerson,G.R.,Coats,D.E.,Dang,A.L., Dunn,S.S.,Kehtarnavaz,H.: Two-DimensionalKinetics(TDK)Nozzle Performance ComputerProgram,NAS8-36863,Marchl 989.

3. Muss,J.A.,Nguyen,TV.,Johnson,C.W.: User'sManualforRocketCombustor InteractiveDesign (ROCCID)andAnalysis ComputerProgram, NASAContractorReport 187109,ContractNAS3-25556,May 1991.

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