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b2310453 |
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CoU |
| 005 |
19940908144701.0 |
| 006 |
m d f |
| 007 |
cr |
| 008 |
940908s1987 dcua b b f000 0 eng d |
| 035 |
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|a (OCoLC)ocm31067246
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| 035 |
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|a (GPO)94094960
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| 037 |
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|a N 87-27936
|b NASA
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| 040 |
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|a GPO
|c GPO
|d DLC
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| 049 |
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|a COD9
|a GDWR
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| 074 |
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|a 0830-H-14 (MF)
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| 086 |
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|a NAS 1.26:180280
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| 086 |
0 |
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|a NAS 1.26:180280
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| 100 |
1 |
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|a Colwell, Gene T.
|q (Gene Thomas),
|d 1937-
|0 http://id.loc.gov/authorities/names/no2009121892
|1 http://isni.org/isni/0000000069250359.
|
| 245 |
1 |
0 |
|a Modeling of transient heat pipe operation
|h [microform] :
|b period covered August 13, 1986 through February 18, 1987 /
|c Gene T. Colwell.
|
| 260 |
|
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|a Atlanta, Ga. :
|b Georgia Institute of Technology, School of Mechanical Engineering ;
|a [Washington, D.C.] :
|b [National Aeronautics and Space Administration] ;
|a [Springfield, Va.] :
|b [National Technical Information Service, distributor],
|c [1987]
|
| 300 |
|
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|a 35 pages :
|b illustrations.
|
| 336 |
|
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|a text
|b txt
|2 rdacontent.
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| 337 |
|
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|a microform
|b h
|2 rdamedia.
|
| 338 |
|
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|a microfiche
|b he
|2 rdacarrier.
|
| 490 |
1 |
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|a NASA CR ;
|v 180280.
|
| 500 |
|
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|a Title from label; title page on microfiche not legible.
|
| 500 |
|
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|a "July 1,1987"
|
| 504 |
|
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|a Includes bibliographical references (pages 31-32)
|
| 530 |
|
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|a Distributed to depository libraries in microfiche; also available via the Internet.
|
| 513 |
|
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|a Semi-annual status report;
|b August 13, 1986 through February 18, 1987.
|
| 520 |
3 |
|
|a The use of heat pipes is being considered as a means of reducing the peak temperature and large thermal gradients at the leading edges of reentry vehicles and hypersonic aircraft and in nuclear reactors. In the basic cooling concept, the heat pipe covers the leading edge, a portion of the lower wing surface, and a portion of the upper wing surface. Aerodynamic heat is mainly absorbed at the leading edge and transported through the heat pipe to the upper and lower wing surface, where it is rejected by thermal radiation and convection. Basic governing equations are written to determine the startup, transient, and steady state performance of a haet pipe which has initially frozen alkali-metal as the working fluid.
|
| 533 |
|
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|a Microfiche.
|b [Washington, D.C. :
|c National Aeronautics and Space Administration,
|d 1987]
|e 1 microfiche.
|
| 536 |
|
|
|a NASA grant
|c NAG-1-392.
|
| 650 |
|
0 |
|a Heat pipes.
|0 http://id.loc.gov/authorities/subjects/sh85059798.
|
| 650 |
|
0 |
|a Heat
|x Transmission.
|0 http://id.loc.gov/authorities/subjects/sh85059767.
|
| 710 |
1 |
|
|a United States.
|b National Aeronautics and Space Administration.
|0 http://id.loc.gov/authorities/names/n78087581
|1 http://isni.org/isni/0000000449071619.
|
| 710 |
2 |
|
|a Georgia Institute of Technology.
|b School of Mechanical Engineering.
|0 http://id.loc.gov/authorities/names/n83156993.
|
| 830 |
|
0 |
|a NASA contractor report ;
|v NASA CR-180280.
|0 http://id.loc.gov/authorities/names/n83825229.
|
| 856 |
4 |
1 |
|u http://hdl.handle.net/2060/19870018503
|z Connect to online resource
|
| 907 |
|
|
|a .b23104533
|b 03-18-20
|c 12-12-95
|
| 998 |
|
|
|a gov
|a web
|b 03-21-95
|c -
|d m
|e -
|f eng
|g gau
|h 0
|i 1
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| 907 |
|
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|a .b23104533
|b 05-09-19
|c 12-12-95
|
| 944 |
|
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|a MARS - RDA ENRICHED
|
| 907 |
|
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|a .b23104533
|b 10-19-09
|c 12-12-95
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| 907 |
|
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|a .b23104533
|b 09-02-08
|c 12-12-95
|
| 999 |
f |
f |
|i 28df61c8-af52-5735-81da-d5c9474863be
|s 41042c58-19a5-5a94-9c95-65250b2930ae
|
| 952 |
f |
f |
|p Can circulate
|a University of Colorado Boulder
|b Boulder Campus
|c Norlin
|d Norlin Library - Government Information - Microform
|e NAS 1.26:180280
|h Superintendent of Documents classification
|i document
|n 1
|
| 952 |
f |
f |
|p Can circulate
|a University of Colorado Boulder
|b Online
|c Online
|d Online
|e NAS 1.26:180280
|h Superintendent of Documents classification
|i web
|n 1
|
