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NACA-TN-3287

Heat transfer from a hemisphere-cylinder equipped with flow-separation spikes

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:11:52Z
date available2017-09-04T17:11:52Z
date copyright01/01/1954
date issued1954
identifier otherYTNUYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/135328
description abstractAverage heat-transfer, temperature-recovery, and pressure-distribution measurements were obtained over the hemispherical nose of a body of revolution both with and without flow-separation spikes. The tests, conducted in a range of Reynolds numbers from 1.55 to 9.85 x 10(5) and from Mach number 0.12 to 5.04, indicated that in supersonic flow the addition of spikes approximately doubles the rate of heat transfer, regardless of spike length.
languageEnglish
titleNACA-TN-3287num
titleHeat transfer from a hemisphere-cylinder equipped with flow-separation spikesen
typestandard
page30
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1954
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsBLUNT
subject keywordsBODIES
subject keywordsCONFIGURATIONS
subject keywordsCYLINDER
subject keywordsCYLINDRICAL
subject keywordsDISTRIBUTION
subject keywordsFLOW
subject keywordsFOREBODIES
subject keywordsHEAT
subject keywordsHEMISPHERE
subject keywordsMACH
subject keywordsMODELS
subject keywordsNOSES
subject keywordsNUMBER
subject keywordsPRESSURE
subject keywordsRECOVERY
subject keywordsREVOLUTION
subject keywordsREYNOLDS
subject keywordsSEPARATED
subject keywordsSPIKES
subject keywordsSUPERSONIC
subject keywordsTEMPERATURE
subject keywordsTESTS
subject keywordsTRANSFER
subject keywordsTUNNEL
subject keywordsWIND


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