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NACA-TR-574

Pressure distribution over an airfoil section with a flap and ta

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:30:24Z
date available2017-09-04T18:30:24Z
date copyright01/01/1937
date issued1937
identifier otherIWITDEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=autho4703ear3081D206/handle/yse/212693
description abstractReport presents the results of wind tunnel tests made in the NACA 7 by 10-foot wind tunnel of a Clark Y airfoil with a flap and an inset tab. The pressures were measured on both the upper and lower surfaces at one chord section. Calculations were made of the normal-force and pitching-moment coefficients of the airfoil section with flap section with tab, and the normal-force and hinge-moments coefficients of the tab alone. In addition, comparisons were made of the theoretical and experimental values for an airfoil with a multiply hinged flap system.
languageEnglish
titleNACA-TR-574num
titlePressure distribution over an airfoil section with a flap and taen
typestandard
page18
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1937
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRFOILS
subject keywordsCOEFFICIENTS
subject keywordsCOMPARISON
subject keywordsCONTROL
subject keywordsDISTRIBUTION
subject keywordsEXPERIMENTATION
subject keywordsFLAPS
subject keywordsLIFT
subject keywordsMOMENTS
subject keywordsPITCHING
subject keywordsPRESSURE
subject keywordsSURFACES
subject keywordsTABS
subject keywordsTESTS
subject keywordsTHEORIES
subject keywordsTORQUE
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING


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