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NACA-TN-1406

High-speed wind-tunnel tests of an NACA 16-009 airfoil having a 32.9-percent-chord flap with an overhang 20.7 percent of the flap chord

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:12:12Z
date available2017-09-04T17:12:12Z
date copyright01/01/1947
date issued1947
identifier otherYUSSYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/135748
description abstractINTRODUCTION
Reports on the performance of high-speed fighter airplanes and recent wind-tunnel investigations at high Mach numbers have indicated large adverse changes in control characteristics due to the effects of compressibility. The tests on a 5-inch-chord two-dimensional flapped NACA 16-009 airfoil reported herein are the first of a series of tests being conducted in the Langley 24-inch high-speed tunnel to investigate these effects.
languageEnglish
titleNACA-TN-1406num
titleHigh-speed wind-tunnel tests of an NACA 16-009 airfoil having a 32.9-percent-chord flap with an overhang 20.7 percent of the flap chorden
typestandard
page39
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAIRFOILS
subject keywordsBALANCED
subject keywordsCHAR
subject keywordsCHARACTERISTICS
subject keywordsCOMPRESSIBILITY
subject keywordsEFFECT
subject keywordsFLAPS
subject keywordsGAPS
subject keywordsHIGH
subject keywordsMOMENTS
subject keywordsNACA
subject keywordsOVERHANG
subject keywordsROUGHNESS
subject keywordsSPEED
subject keywordsSURFACE
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING


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