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NACA-TR-267

Drag of wings with end plates

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:52:23Z
date available2017-09-04T17:52:23Z
date copyright01/01/1928
date issued1928
identifier otherFBXUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=authoCA5893FD081D49A96159DD6EFDEC014A/handle/yse/175611
description abstractIn this report a formula for calculating the induced drag of multiplanes with end plates is derived. The frictional drag of the end plates are used, is sufficiently large to increase the efficiency of the wing. Curves showing the reduction of drag for monoplanes and biplanes are constructed; the influence of gap-chord ratio, aspect ratio, and height of end plate are determined for typical cases. The method of obtaining the reduction of drag for a multiplane is described. Comparisons are made of calculated and experimental results obtained in wind tunnel tests with airfoils of various aspect ratios and end plates of various sizes. The agreement between calculated and experimental results is good. Analysis of the experimental results shows that the shape and section of the end plates are important.
languageEnglish
titleNACA-TR-267num
titleDrag of wings with end platesen
typestandard
page13
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1928
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsASPECT
subject keywordsBIPLANES
subject keywordsCOMPARISON
subject keywordsCOMPUTATION
subject keywordsDRAG
subject keywordsEND
subject keywordsFORMULAS
subject keywordsMATHEMATICS
subject keywordsMONOPLANES
subject keywordsPLATES
subject keywordsRATIO
subject keywordsREDUCTION
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWINGS


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