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NASA-TM-X-74018

Low-speed wind tunnel results for a modified 13-percent-thick airfoil

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:30:15Z
date available2017-09-04T18:30:15Z
date copyright01/01/1977
date issued1977
identifier otherIVTKAEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=autho1216AF679D/handle/yse/212490
description abstractAbstract: Wind-tunnel tests were conducted to evaluate the effects on performance of modifying a 13-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the aft upper surface pressure gradient and hence delay boundary layer separation at typical lift coefficients for light general aviation airplanes. The tests were conducted at a Mach number of 0.15 or less over a Reynolds number range from about 1,000,000 to 9,000,000.
languageEnglish
titleNASA-TM-X-74018num
titleLow-speed wind tunnel results for a modified 13-percent-thick airfoilen
typestandard
page40
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1977
contenttypefulltext
subject keywordsAIRCRAFT
subject keywordsAIRFOIL
subject keywordsAIRFOILS
subject keywordsAVIATION
subject keywordsBOUNDARY
subject keywordsDISTRIBUTION
subject keywordsGENERAL
subject keywordsLAYER
subject keywordsLOW
subject keywordsNUMBER
subject keywordsPRESSURE
subject keywordsPROFILES
subject keywordsREYNOLDS
subject keywordsSEPARATION
subject keywordsSPEED
subject keywordsTUNNELS
subject keywordsWIND


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