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100   $a20111115j196808    ua             0
101 0 $aeng
135   $aur|||||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aCold-air investigation of effects of partial admission on performance of 3.75-inch mean-diameter single-stage axial-flow turbine /$fby Hugh A. Klassen
210  1$aWashington, D.C. :$cNational Aeronautics and Space Administration,$dAugust 1968.
215   $a1 online resource (19 pages) $cillustrations
225 1 $aNASA technical note ;$vTN D-4700
300   $a"August 1968."
320   $aIncludes bibliographical references (page 19).
606   $aTurbines$xBlades$xTesting
606   $aTurbines$xDesign and construction
606   $aTurbines$xBlades$xTesting$2fast
606   $aTurbines$xDesign and construction$2fast
615  0$aTurbines$xBlades$xTesting.
615  0$aTurbines$xDesign and construction.
615  7$aTurbines$xBlades$xTesting.
615  7$aTurbines$xDesign and construction.
700   $aKlassen$b Hugh A.$01404884
712 02$aUnited States.$bNational Aeronautics and Space Administration,
712 02$aLewis Research Center.
801  0$bOCLCE
801  1$bOCLCE
801  2$bOCLCQ
801  2$bOCLCF
801  2$bOCLCO
801  2$bOCLCQ
801  2$bGPO
906   $aBOOK
912   $a9910715197003321
996   $aCold-air investigation of effects of partial admission on performance of 3.75-inch mean-diameter single-stage axial-flow turbine$93480375
997   $aUNINA