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NACA-TN-2146

On the effect of subsonic trailing edges on damping in roll and pitch of thin sweptback wings in a supersonic stream

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:23:22Z
date available2017-09-04T18:23:22Z
date copyright01/01/1950
date issued1950
identifier otherAHBUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsery=autho47037D83FCDCAC42/handle/yse/205807
description abstractThe principal effect of subsonic trailing edges on the damping in roll and pitch of thin sweptback wings in a supersonic stream is evaluated with the aid of some conical and quasi-conical flows previously derived. This effect is expressed in the form of approximate correction terms to be added to the corresponding expressions that are obtained when the trailing-edge disturbance is ignored. The results are limited to those plan forms and Mach numbers for which the trailing-edge disturbance does not extend beyond the leading edge and for which the areas of mutual interference between tips and trailing edge is not large. Practical applicability is subject to the limitations of linearized potential theory.
languageEnglish
titleNACA-TN-2146num
titleOn the effect of subsonic trailing edges on damping in roll and pitch of thin sweptback wings in a supersonic streamen
typestandard
page30
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1950
contenttypefulltext
subject keywordsCONICAL
subject keywordsDAMPING
subject keywordsEDGES
subject keywordsFLOW
subject keywordsLINEAR
subject keywordsPITCH
subject keywordsROLL
subject keywordsSTABILITY
subject keywordsSUPERSONIC
subject keywordsSWEPTBACK
subject keywordsTHEORIES
subject keywordsTRAILING
subject keywordsWINGS


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