LEADER 01817oam  2200529   450 
001 9910715970103321
005 20210402140027.0
035   $a(CKB)5470000002516392
035   $a(OCoLC)760927075
035   $a(EXLCZ)995470000002516392
100   $a20111114j196808    ua             0
101 0 $aeng
135   $aur|||||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aCalibration of 30° included-angle cone for determining local flow conditions in Mach number range of 1.51 to 3.51 /$fWalter A. Vahl and Robert L. Weirich
210  1$aWashington, D.C. :$cNational Aeronautics and Space Administration,$dAugust 1968.
215   $a1 online resource (39 pages) $cillustrations
225 1 $aNASA/TN ;$vD-4679
300   $a"August 1968."
320   $aIncludes bibliographical references (page 11).
606   $aBase flow$2nasat
606   $aSupersonic transports$2nasat
606   $aBase flow (Aerodynamics)$2fast
606   $aCone$xAerodynamics$2fast
606   $aMach number$2fast
606   $aSupersonic transport planes$2fast
615  7$aBase flow.
615  7$aSupersonic transports.
615  7$aBase flow (Aerodynamics)
615  7$aCone$xAerodynamics.
615  7$aMach number.
615  7$aSupersonic transport planes.
700   $aVahl$b Walter A.$01410462
702   $aWeirich$b Robert L.
712 02$aUnited States.$bNational Aeronautics and Space Administration,
801  0$bOCLCE
801  1$bOCLCE
801  2$bOCLCQ
801  2$bOCLCF
801  2$bOCLCQ
801  2$bGPO
906   $aBOOK
912   $a9910715970103321
996   $aCalibration of 30° included-angle cone for determining local flow conditions in Mach number range of 1.51 to 3.51$93499148
997   $aUNINA