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100   $a20100826d1992      ua             0
101 0 $aeng
135   $aurbn|||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aPerformance comparison of axisymmetric and three-dimensional hydrogen film coolant injection in a 110N hydrogen/oxyen rocket$b[electronic resource] /$fLynn A. Arrington and Brian D. Reed
210  1$a[Cleveland, Ohio] :$cNational Aeronautics and Space Administration, Lewis Research Center,$d[1992?]
215   $a1 online resource (20 pages) $cdigital, PDF file
225 1 $aNASA technical memorandum ;$v105967
300   $aTitle from title screen (viewed Aug. 25, 2010).
320   $aIncludes bibliographical references (pages 8-9).
410  0$aNASA technical memorandum ;$v105967.
606   $aAxisymmetric flow$2nasat
606   $aCoolants$2nasat
606   $aFilm cooling$2nasat
606   $aFluid injection$2nasat
606   $aHydrogen$2nasat
606   $aHydrogen oxygen engines$2nasat
606   $aPropulsion system performance$2nasat
606   $aReacting flow$2nasat
606   $aThree dimensional flow$2nasat
615  7$aAxisymmetric flow.
615  7$aCoolants.
615  7$aFilm cooling.
615  7$aFluid injection.
615  7$aHydrogen.
615  7$aHydrogen oxygen engines.
615  7$aPropulsion system performance.
615  7$aReacting flow.
615  7$aThree dimensional flow.
700   $aArrington$b Lynn A$01386855
701   $aReed$b Brian D$01391757
712 02$aLewis Research Center.
801  0$bGPO
801  1$bGPO
906   $aBOOK
912   $a9910699539803321
996   $aPerformance comparison of axisymmetric and three-dimensional hydrogen film coolant injection in a 110N hydrogen$93445795
997   $aUNINA