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NACA-TR-942

Investigation in the Langley 19-foot pressure tunnel of two wings of NACA 65-210 and 64-210 airfoil sections with various type flaps

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:48:24Z
date available2017-09-04T15:48:24Z
date copyright01/01/1949
date issued1949
identifier otherQAXUYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/51298
description abstractReport presents the results of an investigation conducted in the Langley 19-foot pressure tunnel to determine the maximum lift and stalling characteristics of two thin wings equipped with several types of flaps. Split, single slotted, and double slotted flaps were tested on one wing which had NACA 65-210 airfoil sections and split and double slotted flaps were tested on the other, which had NACA 64-210 airfoil sections. Both wings were zero sweep, an aspect ratio of 9, and a taper ratio of 0.4.
languageEnglish
titleNACA-TR-942num
titleInvestigation in the Langley 19-foot pressure tunnel of two wings of NACA 65-210 and 64-210 airfoil sections with various type flapsen
typestandard
page23
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1949
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAERODYNAMICS
subject keywordsAIRFOIL
subject keywordsAIRFOILS
subject keywordsCOEFFICIENTS
subject keywordsCONFIGURATIONS
subject keywordsEDGES
subject keywordsEFFECT
subject keywordsFLAPS
subject keywordsFLOW
subject keywordsINTERACTIONAL
subject keywordsINTERFERENCE
subject keywordsLEADING
subject keywordsLIFT
subject keywordsPROFILES
subject keywordsROUGHNESS
subject keywordsSCALE
subject keywordsSLOTS
subject keywordsSPLIT
subject keywordsSTALLING
subject keywordsSUPERSONIC
subject keywordsSURFACE
subject keywordsTESTS
subject keywordsTHIN
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING
subject keywordsWINGS


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