LEADER 02926oam 2200637 450 001 9910716019603321 005 20210601091751.0 035 $a(CKB)5470000002517912 035 $a(OCoLC)23137432$z(OCoLC)761198139 035 $a(EXLCZ)995470000002517912 100 $a19910222j197211 ua 0 101 0 $aeng 135 $aur||||||||||| 181 $ctxt$2rdacontent 182 $cc$2rdamedia 183 $acr$2rdacarrier 200 10$aEffective thermal conductivities of four metal-ceramic composite coatings in hydrogen-oxygen rocket firings /$fby Ralph L. Schacht, Harold G. Price, Jr., and Richard J. Quentmeyer 210 1$aWashington, D.C. :$cNational Aeronautics and Space Administration,$dNovember 1972. 215 $a1 online resource (41 pages) $cillustrations 225 1 $aNASA/TN ;$vD-7055 300 $a"November 1972." 320 $aIncludes bibliographical references (page 18). 330 $aAn experimental investigation was conducted to determine the effective conductivities of four plasma-arc-sprayed, metal-ceramic gradated coatings on hydrogen-oxygen thrust chambers. The effective thermal conductivities were not a function of pressure or oxidant-to-fuel ratio. The various materials that made up these composites do not seem to affect the thermal conductivity values as much as the differences in the thermal conductivities of the parent materials would lead one to expect. Contact resistance evolving from the spraying process seems to be the controlling factor. The thermal conductivities of all the composites tested fell in the range of 0.75 to 7.5 watts per meter kelvin. 606 $aRocket firing$2nasat 606 $aAeronautics$2nasat 606 $aCoatings$xThermal properties$xTesting 606 $aHeat$xTransmission 606 $aComposite materials$xEffect of temperature on$xTesting 606 $aRockets (Aeronautics)$xNozzles 606 $aHeat$xTransmission$2fast 606 $aRockets (Aeronautics)$xNozzles$2fast 615 7$aRocket firing. 615 7$aAeronautics. 615 0$aCoatings$xThermal properties$xTesting. 615 0$aHeat$xTransmission. 615 0$aComposite materials$xEffect of temperature on$xTesting. 615 0$aRockets (Aeronautics)$xNozzles. 615 7$aHeat$xTransmission. 615 7$aRockets (Aeronautics)$xNozzles. 700 $aSchacht$b Ralph L.$01397472 702 $aPrice$b Harold G. 702 $aQuentmeyer$b Richard J. 712 02$aUnited States.$bNational Aeronautics and Space Administration, 801 0$bABC 801 1$bABC 801 2$bAD# 801 2$bOCLCE 801 2$bOCLCQ 801 2$bOCLCO 801 2$bOCLCQ 801 2$bOCLCF 801 2$bGPO 906 $aBOOK 912 $a9910716019603321 996 $aEffective thermal conductivities of four metal-ceramic composite coatings in hydrogen-oxygen rocket firings$93459151 997 $aUNINA