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NACA-TR-1386

Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 7.4

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:34:10Z
date available2017-09-04T16:34:10Z
date copyright01/01/1958
date issued1958
identifier otherUWITDEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/97572
description abstractExperimental drag measurements at zero angle of attack for various theoretical minimum drag nose shapes, hemispherically blunted cones, and other more common profiles of fineness ratios of about 3 are compared with theoretical results for a Mach number and Reynolds number range of 1.24 to 7.4 and 1.0 x 10 to the 6th power to 7.5 x 10 to the 6th power (based on body length), respectively. The results of experimental pressure-distribution measurements are used for the development of an empirical expression for predicting the pressure drag of hemispherically blunted cones.
languageEnglish
titleNACA-TR-1386num
titleInvestigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 7.4en
typestandard
page18
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1958
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAXISYMMETRIC
subject keywordsBLUNT
subject keywordsBODIES
subject keywordsCOMPUTATIONAL
subject keywordsCONES
subject keywordsDISTRIBUTION
subject keywordsDRAG
subject keywordsDYNAMICS
subject keywordsFINENESS
subject keywordsFLUID
subject keywordsFOREBODIES
subject keywordsFRICTION
subject keywordsMACH
subject keywordsMODELS
subject keywordsNOSES
subject keywordsNUMBER
subject keywordsPARABOLIC
subject keywordsPRESSURE
subject keywordsRATIO
subject keywordsREYNOLDS
subject keywordsSKIN
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWAVE
subject keywordsWIND


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