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NACA-TR-718

Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:44:20Z
date available2017-09-04T16:44:20Z
date copyright01/01/1941
date issued1941
identifier otherVWWUYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/107705
description abstractA pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a 25.66-percent-chord slotted flap and a 20-percent-chord split flap. Pressures were measured on both the upper and the lower surfaces of the main airfoil and the flaps for several angles of attack and at several flap settings. The data, presented as pressure diagrams and as graphs of the section coefficients for the flap alone and for the airfoil-flap combinations, are applicable to rib and flap design for a combination of a thick airfoil and a slotted or a split flap. The results of previous tests of a NACA 23012 airfoil with a slotted flap are compared with the present results.
languageEnglish
titleNACA-TR-718num
titlePressure distribution over an NACA 23012 airfoil with a slotted and a split flapen
typestandard
page26
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1941
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsAIRFOIL
subject keywordsAIRFOILS
subject keywordsANGLE
subject keywordsATTACK
subject keywordsCENTER
subject keywordsCHORDS
subject keywordsCOEFFICIENTS
subject keywordsDESIGN
subject keywordsDISTRIBUTION
subject keywordsFLAPS
subject keywordsFORCE
subject keywordsGEOMETRY
subject keywordsLOADS
subject keywordsMOMENTS
subject keywordsPITCHING
subject keywordsPRESSURE
subject keywordsPROFILES
subject keywordsSLOTS
subject keywordsSPLIT
subject keywordsSTRUCTURES
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING


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