LEADER 00857nam0-2200313---450- 001 990008859190403321 005 20091130120120.0 010 $a978-1-4051-6022-3 035 $a000885919 035 $aFED01000885919 035 $a(Aleph)000885919FED01 035 $a000885919 100 $a20090527d2007----km-y0itay50------ba 101 0 $aeng 102 $aUS 105 $aa-------001yy 200 1 $aMaking up the mind$ehow the brain creates our mental world$fChris Frith 210 $aOxford$cBlackwell$dİ2007 215 $aXII, 234 p.$cill.$d23 cm 610 0 $aMente e cervello 676 $a612.82 700 1$aFrith,$bChristopher D.$0421346 801 0$aIT$bUNINA$gRICA$2UNIMARC 901 $aBK 912 $a990008859190403321 952 $a612.82-FRI-1$b5609$fSC1 959 $aSC1 996 $aMaking up the mind$9804353 997 $aUNINA LEADER 01974oam 2200589 450 001 9910715170603321 005 20201211125543.0 035 $a(CKB)5470000002508306 035 $a(OCoLC)761497571 035 $a(EXLCZ)995470000002508306 100 $a20111115j196808 ua 0 101 0 $aeng 135 $aur||||||||||| 181 $ctxt$2rdacontent 182 $cc$2rdamedia 183 $acr$2rdacarrier 200 10$aEffect of hinge-line bleed on heat transfer and pressure distribution over a wedge-flap combination at Mach 10.4 /$fby H. Harris Hamilton, and J. David Dearing 210 1$aWashington, D.C. :$cNational Aeronautics and Space Administration,$dAugust 1968. 215 $a1 online resource (44 pages) $cillustrations 225 1 $aNASA technical note ;$vTN D-4686 300 $a"August 1968." 320 $aIncludes bibliographical references (pages 18-21). 606 $aBoundary layer control 606 $aFlaps (Airplanes) 606 $aWedges 606 $aAircraft separation 606 $aAircraft separation$2fast 606 $aBoundary layer control$2fast 606 $aFlaps (Airplanes)$2fast 606 $aWedges$2fast 615 0$aBoundary layer control. 615 0$aFlaps (Airplanes) 615 0$aWedges. 615 0$aAircraft separation. 615 7$aAircraft separation. 615 7$aBoundary layer control. 615 7$aFlaps (Airplanes) 615 7$aWedges. 700 $aHamilton$b H. Harris$01405571 702 $aDearing$b J. David 712 02$aUnited States.$bNational Aeronautics and Space Administration, 712 02$aLangley Research Center. 801 0$bOCLCE 801 1$bOCLCE 801 2$bOCLCQ 801 2$bOCLCF 801 2$bOCLCQ 801 2$bGPO 906 $aBOOK 912 $a9910715170603321 996 $aEffect of hinge-line bleed on heat transfer and pressure distribution over a wedge-flap combination at Mach 10.4$93482420 997 $aUNINA