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NACA-TN-2483

Effect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability tunnel

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:00:09Z
date available2017-09-04T16:00:09Z
date copyright01/01/1951
date issued1951
identifier otherRHLUYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/63299
description abstractResults are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included.
languageEnglish
titleNACA-TN-2483num
titleEffect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability tunnelen
typestandard
page20
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1951
contenttypefulltext
subject keywordsAERODYNAMICS
subject keywordsAIRPLANES
subject keywordsCOMBINATIONS
subject keywordsCOMPLETE
subject keywordsDAMPING
subject keywordsDERIVITIVES
subject keywordsFUSELAGE
subject keywordsLONGITUDINAL
subject keywordsRESEARCH
subject keywordsSTABILITY
subject keywordsSTATIC
subject keywordsSWEEP
subject keywordsTAIL
subject keywordsTECHNIQUES
subject keywordsTUNNELS
subject keywordsWIND
subject keywordsWING
subject keywordsWINGS


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