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NASA-CR-3081

Wind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoile

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:03:37Z
date available2017-09-04T15:03:37Z
date copyright01/01/1979
date issued1979
identifier otherKWMKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/829
description abstractForce and surface pressure distributions were measured for the 21% LS(1)-0421 modified airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted at a Reynolds number of 2.2 x 10 to the 6th power and a Mach number of 0.13. The lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions are included in the results. Incremental performance of flap and aileron are discussed and compared to the GA(W)-2 airfoil. Spoiler control which shows a slight reversal tendency at high alpha, is examined.
languageEnglish
titleNASA-CR-3081num
titleWind tunnel force and pressure tests of a 21% thick general aviation airfoil with 20% aileron, 25% slotted flap and 10% slot-lip spoileen
typestandard
page116
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1979
contenttypefulltext
subject keywordsAILERONS
subject keywordsAIRFOIL
subject keywordsDISTRIBUTION
subject keywordsDRAG
subject keywordsGAW
subject keywordsLIFT
subject keywordsMOMENTS
subject keywordsPITCHING
subject keywordsPRESSURE
subject keywordsSLOT
subject keywordsSLOTS
subject keywordsSPOILER
subject keywordsSPOILERS
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND


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