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100   $a20090219d1943----km-y0itay50------ba
101 0 $aita
102   $aIT
105   $ay-------001yy
200 1 $aCodice del diritto di autore$ecomm. della nuova l. 22 apr. 1941-19., n. 633$ecorredato dei lavori preparatori e di un indice analitico della leggi interessanti la materia$fEduardo Piola Caselli
210   $aTorino$cUTET$d1943
215   $aXVII, 760 p.
676   $a346$v11 rid.$zita
702  1$aPiola Caselli,$bEduardo$f<1868-1943>
710 02$aItalia$0423419
801  0$aIT$bUNINA$gRICA$2UNIMARC
901   $aBK
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952   $aVIII I$b25369$fFGBC
959   $aFGBC
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997   $aUNINA

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100   $a20200602d1940      ua             0
101 0 $aeng
135   $aurbn|||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aPressure-distributioin investigation of an N.A.C.A. 0009 airfoil with an 80-percent-chord plain flap and three tabs /$fby Milton B. Ames, Jr., and Richard I. Sears
210  1$aWashington, [D.C.] :$cNational Advisory Committee for Aeronautics,$d1940.
215   $a1 online resource (11 pages, 23 unnumbered pages) $cillustrations
225 1 $aTechnical note / National Advisory Committee for Aeronautics ;$vno. 761
300   $a"May 1940."
300   $aNo Federal Depository Library Program (FDLP) item number.
320   $aIncludes bibliographical references (page 11).
606   $aAirplanes$xWings$xTesting
606   $aFlaps (Airplanes)
606   $aAirplanes$xControl surfaces
606   $aAerodynamic load
606   $aAerodynamic load$2fast
606   $aAirplanes$xControl surfaces$2fast
606   $aAirplanes$xWings$xTesting$2fast
606   $aFlaps (Airplanes)$2fast
615  0$aAirplanes$xWings$xTesting.
615  0$aFlaps (Airplanes)
615  0$aAirplanes$xControl surfaces.
615  0$aAerodynamic load.
615  7$aAerodynamic load.
615  7$aAirplanes$xControl surfaces.
615  7$aAirplanes$xWings$xTesting.
615  7$aFlaps (Airplanes)
700   $aAmes$b Milton B.$cJr.,$01401876
702   $aSears$b Richard I.
712 02$aUnited States.$bNational Advisory Committee for Aeronautics,
801  0$bTRAAL
801  1$bTRAAL
801  2$bOCLCO
801  2$bOCLCF
801  2$bXFF
801  2$bOCLCO
801  2$bGPO
906   $aBOOK
912   $a9910717125103321
996   $aPressure-distributioin investigation of an N.A.C.A. 0009 airfoil with an 80-percent-chord plain flap and three tabs$93495043
997   $aUNINA