Design, analysis, and testing of refractory metal heat pipes using lithium as the working fluid
Author:
Affiliation:
1. Teledyne Wah Chang, Albany, OR
2. Boeing Military Airplanes, Seattle, WA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-1400
Reference8 articles.
1. Camarda, C. J. "AerothermalTests of a Heat Pipe Cooled Leading Edge at Mach T, NASA TP 1320,1978.
2. Camarda, C. J. and Masek, R. V. "Design, Analysis,and Tests of a ShuttleType Heat Pipe Cooled Leading Edge", AIAA 81-4020, J. Spacecraft,vol. 18,no. 1,1981.
3. SiIverstein, C. C. "AFeasibility Studyof Heat Pipe Cooled Leading Edges for Hypersonic CruiseAircraft",NASA CR-1857,Nov. 1971.
4. Clark, L. T., and Glenn, G. S. "Design, Analysisand Testingof LiquidMetalHeat Pipes forApplication to HypersonicVehicles",AIAA88-2679,1988.
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