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NACA-ARR-L5F23

Lifting-surface-theory values of the damping in roll and of the parameter used in estimating aileron stick forces

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:10:53Z
date available2017-09-04T17:10:53Z
date copyright01/01/1945
date issued1945
identifier otherYRCTUDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/134479
description abstractINTRODUCTION
One of the many aerodynamic problems for which a theoretical solution by means of lifting-line theory might be expected to be inadequate is the case of a wing in steady roll. Robert T. Jones has obtained in an unpublished analysis similar to that of reference 1 a correction to the lifting-line-theory values of the damping in roll that amounts to an B-percent reduction in the values for a wing of aspect ratio 6. Still more accurate values may be obtained by use of lifting-surface theory.
languageEnglish
titleNACA-ARR-L5F23num
titleLifting-surface-theory values of the damping in roll and of the parameter used in estimating aileron stick forcesen
typestandard
page56
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1945
contenttypefulltext
subject keywordsAILERON
subject keywordsAILERONS
subject keywordsAIRFOILS
subject keywordsANALOGY
subject keywordsASPECT
subject keywordsCONTROL
subject keywordsCONTROLS
subject keywordsDAMPING
subject keywordsDISTRIBUTION
subject keywordsDOWNWASH
subject keywordsELECTROMAGNETIC
subject keywordsELLIPTICAL
subject keywordsFORCES
subject keywordsHINGE
subject keywordsLIFT
subject keywordsLIFTING
subject keywordsMETHOD
subject keywordsMOMENTS
subject keywordsRATIO
subject keywordsROLL
subject keywordsSTICKS
subject keywordsSURFACE
subject keywordsTHEORIES
subject keywordsWINGS


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