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NACA-TN-3911

A method for predicting lift increments due to flap deflection at low angles of attack in incompressible flow

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:42:30Z
date available2017-09-04T18:42:30Z
date copyright01/01/1957
date issued1957
identifier otherJZNUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/223921
description abstractA method is presented for estimating the lift due to flap deflection at low angles of attack in incompressible flow. In this method provision is made for the use of incremental section-lift data for estimating the effectiveness of high-lift flaps. The method is applicable to swept wings of any aspect ratio or taper ratio. The present method differs from other current methods mainly in its ease of application and its more general application. Also included is a simplified method of estimating the lift-curve slope throughout the subsonic speed range.
languageEnglish
titleNACA-TN-3911num
titleA method for predicting lift increments due to flap deflection at low angles of attack in incompressible flowen
typestandard
page30
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1957
contenttypefulltext
subject keywordsASPECT
subject keywordsCOMPLETE
subject keywordsCONTROL
subject keywordsEDGE
subject keywordsEFFECTS
subject keywordsFAPS
subject keywordsFLAP
subject keywordsMACH
subject keywordsNUMBER
subject keywordsRATIO
subject keywordsSWEEP
subject keywordsTAPER
subject keywordsTHEORY
subject keywordsTRIALING
subject keywordsTWIST
subject keywordsTYPE
subject keywordsWINGS


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