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NASA-TP-1919

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:03:14Z
date available2017-09-04T16:03:14Z
date copyright01/01/1981
date issued1981
identifier otherRPWWAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/66473
description abstractWind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.
languageEnglish
titleNASA-TP-1919num
titleWind-tunnel results for a modified 17-percent-thick low-speed airfoil sectionen
typestandard
page86
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1981
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsAIRFOIL
subject keywordsAVIATION
subject keywordsCOEFFICIENTS
subject keywordsDRAG
subject keywordsFLOW
subject keywordsGENERAL
subject keywordsGRADIENTS
subject keywordsLIFT
subject keywordsLOW
subject keywordsNUMBER
subject keywordsPRESSURE
subject keywordsPROFILES
subject keywordsRATIO
subject keywordsREYNOLDS
subject keywordsSENSORS
subject keywordsSPEED
subject keywordsSTABILITY
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsTURBULENT
subject keywordsWIND


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