MARC Record from marc_columbia

LEADER: 03227cam a2200565 i 4500
001 11608459
005 20221203224052.0
006 m o d
007 cr cnu---unuuu
008 150825s1949 dcu ob f000 0 eng d
035 $a(OCoLC)ocn919161696
035 $a(NNC)11608459
040 $aKNOVL$beng$erda$epn$cKNOVL$dZCU$dTFW$dUAB$dDKU$dOCLCQ$dCEF$dRRP$dYOU$dS2H$dOCLCO$dOCLCQ$dUPM
020 $a9781680156461$q(electronic bk.)
020 $a1680156462$q(electronic bk.)
035 $a(OCoLC)919161696
050 4 $aTL501$b.U52 1949eb
082 04 $a629.4$223
086 0 $aY 3.N 21/5:5/934
049 $aZCUA
100 1 $aHoff, Nicholas J.$q(Nicholas John),$d1906-$eauthor.
245 10 $aRecommendations for numerical solution of reinforced-panel and fuselage-ring problems /$cby N.J. Hoff and Paul A. Libby.
264 1 $aWashington, D.C. :$bU.S. Government Printing Office,$c1949.
300 $a1 online resource (29 pages)
336 $atext$btxt$2rdacontent
337 $acomputer$bc$2rdamedia
338 $aonline resource$bcr$2rdacarrier
490 1 $aReport / National Advisory Committee for Aeronautics ;$vnumber 934
504 $aIncludes bibliographical references (page 21).
588 0 $aPrint version record.
520 $aProcedures are recommended for solving the equations of equilibrium of reinforced panels and isolated fuselage rings as represented by the external loads and the operations table established according to Southwell's method. From the solution of these equations the stress distribution can be easily determined. The method of systematic relaxations, the matrix-calculus method, and several other methods applicable in special cases are discussed. Definite recommendations are made for obtaining the solution of reinforced-panel problems which are generally designated as shear lag problems. The procedures recommended are demonstrated in the analysis of a number of panels. In the case of fuselage rings it is not possible to make definite recommendations for the solution of the equilibrium equations for all rings and loadings. --$cProvided by publisher.
650 0 $aAeronautics$xResearch.
650 0 $aAirplanes$xFuselage.
650 0 $aAirplanes$xDesign and construction.
650 6 $aAéronautique$xRecherche.
650 6 $aAvions$xFuselage.
650 6 $aAvions$xConception et construction.
650 7 $afuselages.$2aat
650 7 $aAeronautics$xResearch.$2fast$0(OCoLC)fst00798376
650 7 $aAirplanes$xDesign and construction.$2fast$0(OCoLC)fst00803132
650 7 $aAirplanes$xFuselage.$2fast$0(OCoLC)fst00803220
655 0 $aElectronic books.
655 4 $aElectronic books.
700 1 $aLibby, Paul A.,$eauthor.
710 1 $aUnited States.$bNational Advisory Committee for Aeronautics.
710 2 $aPolytechnic Institute of Brooklyn.
776 08 $iPrint version:$aHoff, N.J.$tRecommendations for numerical solution of reinforced-panel and fuselage-ring problems$w(OCoLC)46869359
830 0 $aReport (United States. National Advisory Committee for Aeronautics) ;$vno. 934.
856 40 $uhttp://www.columbia.edu/cgi-bin/cul/resolve?clio11608459$zACADEMIC - Aerospace & Radar Technology
852 8 $blweb$hEBOOKS