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100   $a20111115j196810    ua             0
101 0 $aeng
135   $aur|||||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aFlow-field properties near an arrow-wing--body model at Mach numbers of 1.60, 2.36, and 2.96 /$fby Robert L. Weirich and Walter A. Vahl
210  1$aWashington, D.C. :$cNational Aeronautics and Space Administration,$dOctober 1968.
215   $a1 online resource (135 pages) $cillustrations
225 1 $aNASA technical note ;$vTN D-4809
300   $a"October 1968."
320   $aIncludes bibliographical references (page 12).
606   $aSupersonic wind tunnels$xTesting
606   $aSupersonic planes$xDesign and construction
606   $aSupersonic planes$xTesting
606   $aSupersonic planes$xDesign and construction$2fast
606   $aSupersonic wind tunnels$xTesting$2fast
615  0$aSupersonic wind tunnels$xTesting.
615  0$aSupersonic planes$xDesign and construction.
615  0$aSupersonic planes$xTesting.
615  7$aSupersonic planes$xDesign and construction.
615  7$aSupersonic wind tunnels$xTesting.
700   $aWeirich$b Robert L.$01398246
702   $aVahl$b Walter A.
712 02$aUnited States.$bNational Aeronautics and Space Administration,
801  0$bOCLCE
801  1$bOCLCE
801  2$bOCLCQ
801  2$bOCLCF
801  2$bGPO
906   $aBOOK
912   $a9910714050603321
996   $aFlow-field properties near an arrow-wing--body model at Mach numbers of 1.60, 2.36, and 2.96$93461227
997   $aUNINA