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NACA-TN-1463

Investigation of NACA 65 (112) A111 (approx.) airfoil with 0.35-chord slotted flap at Reynolds numbers up to 25 million

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:46:50Z
date available2017-09-04T18:46:50Z
date copyright01/01/1947
date issued1947
identifier otherAMWSYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsessionid=47037D83FCDCAC426159DD6E273C9FCD/handle/yse/228018
description abstractAn investigation has been made in the Langley two-dimensional low-turbulence tunnel and the Langley two-dimensional low-turbulence pressure tunnel to determine the highest maximum lift configurations (ideal configurations) of a 0.35-chord slotted flap on an NACA 65(112)A111 (approx.) airfoil section. The scale effects on the aerodynamic characteristics were determined for Reynolds numbers ranging from 2.4 X 106 to approximately 25.0 X 106.
languageEnglish
titleNACA-TN-1463num
titleInvestigation of NACA 65 (112) A111 (approx.) airfoil with 0.35-chord slotted flap at Reynolds numbers up to 25 millionen
typestandard
page34
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAIRFOILS
subject keywordsCARRIED
subject keywordsCHAR
subject keywordsCOEFFICIENTS
subject keywordsDEFLECTION
subject keywordsDRAG(WING
subject keywordsFLAPS
subject keywordsLIFT
subject keywordsLMAL
subject keywordsLOW
subject keywordsMOMENTS
subject keywordsNACA
subject keywordsNUMBER
subject keywordsPRESSURE
subject keywordsREYNOLDS
subject keywordsSLOTTED
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsTURBULENCE
subject keywordsWIND
subject keywordsWING
subject keywordsWORK


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