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NASA-CR-3449

Calculation of vortex lift effect for cambered wings by the suction analogy

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:29:02Z
date available2017-09-04T15:29:02Z
date copyright01/01/1981
date issued1981
identifier otherNWMKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/30265
description abstractAn improved version of Woodward's chord plane aerodynamic panel method for subsonic and supersonic flow is developed for cambered wings exhibiting edge separated vortex flow, including those with leading edge vortex flaps. The exact relation between leading edge thrust and suction force in potential flow is derived. Instead of assuming the rotated suction force to be normal to wing surface at the leading edge, new orientation for the rotated suction force is determined through consideration of the momentum principle. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semi-empirical method. Comparisons of predicted results with available data in subsonic and supersonic flow are presented.
languageEnglish
titleNASA-CR-3449num
titleCalculation of vortex lift effect for cambered wings by the suction analogyen
typestandard
page86
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1981
contenttypefulltext
subject keywordsANGLE
subject keywordsATTACK
subject keywordsCAMBERED
subject keywordsEDGE
subject keywordsEQUATIONS
subject keywordsFLAPS
subject keywordsFLOW
subject keywordsLEADING
subject keywordsLIFT
subject keywordsPOTENTIAL
subject keywordsSUBSONIC
subject keywordsSUCTION
subject keywordsSUPERSONIC
subject keywordsTHRUST
subject keywordsVORTEX
subject keywordsVORTICES
subject keywordsWINGS


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