LEADER 00908nam--2200349---450- 001 990002021670203316 005 20051209130735.0 035 $a000202167 035 $aUSA01000202167 035 $a(ALEPH)000202167USA01 035 $a000202167 100 $a20040923d1950----km-y0itay0103----ba 101 0 $aita 102 $aIT 105 $a||||||||001yy 200 1 $aDa Monet a Lautrec$fLionello Venturi 205 $a2. 210 $aRoma$cDel Turco$d1950 215 $a217 p.$d24 cm 410 0$12001 454 1$12001 461 1$1001-------$12001 700 1$aVENTURI,$bLionello$023370 801 0$aIT$bsalbc 912 $a990002021670203316 951 $aXII.2.C. 339(VII D 52)$b2131 L.M.$cVII D 959 $aBK 969 $aUMA 979 $aSIAV2$b10$c20040923$lUSA01$h1317 979 $aCOPAT6$b90$c20051209$lUSA01$h1307 996 $aDa Monet a Lautrec$91041757 997 $aUNISA LEADER 01845oam 2200517 450 001 9910716036103321 005 20210521115528.0 035 $a(CKB)5470000002517746 035 $a(OCoLC)1150919530 035 $a(EXLCZ)995470000002517746 100 $a20200416d1935 ua 0 101 0 $aeng 135 $aurbn||||||||| 181 $ctxt$2rdacontent 182 $cc$2rdamedia 183 $acr$2rdacarrier 200 12$aA deflection formula for single-span beams of constant section subjected to combined axial and transverse loads /$fby Walter E. Burke 210 1$aWashington, [D.C.] :$cNational Advisory Committee for Aeronautics,$d1935. 215 $a1 online resource (24 pages, 21 unnumbered pages) $cillustrations 225 1 $aTechnical note / National Advisory Committee for Aeronautics ;$vNo. 540 300 $a"September 1935." 300 $aNo Federal Depository Library Program (FDLP) item number. 320 $aIncludes bibliographical references (page 16). 606 $aAxial loads 606 $aAirplanes$xFuselage 606 $aAeronautics$xResearch 606 $aAeronautics$xResearch$2fast 606 $aAirplanes$xFuselage$2fast 606 $aAxial loads$2fast 615 0$aAxial loads. 615 0$aAirplanes$xFuselage. 615 0$aAeronautics$xResearch. 615 7$aAeronautics$xResearch. 615 7$aAirplanes$xFuselage. 615 7$aAxial loads. 700 $aBurke$b Walter E.$01399821 712 02$aUnited States.$bNational Advisory Committee for Aeronautics, 801 0$bTRAAL 801 1$bTRAAL 801 2$bOCLCO 801 2$bOCLCF 801 2$bGPO 906 $aBOOK 912 $a9910716036103321 996 $aA deflection formula for single-span beams of constant section subjected to combined axial and transverse loads$93465776 997 $aUNINA