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NACA-TN-2175

Effect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane model

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:13:05Z
date available2017-09-04T17:13:05Z
date copyright01/01/1950
date issued1950
identifier otherYXCUYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/136559
description abstractAn investigation has been conducted in the Langley stability tunnel to determine the effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed static-and rolling-stability derivatives of a midwing airplane model.
The results of the investigation show that, at Angeles of attack almost to the angle of maximum lift, there are only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with wing on and with wing off. For this range of angles of attack the contributions of the vertical tail can be estimated fairly accurately by the available procedures.
languageEnglish
titleNACA-TN-2175num
titleEffect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane modelen
typestandard
page48
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1950
contenttypefulltext
subject keywordsCOMBINATION
subject keywordsCOMBINATIONS
subject keywordsDOWNWASH
subject keywordsFUSELAGE
subject keywordsHORIZONTAL
subject keywordsINTERFERENCE
subject keywordsINTERFERENCES
subject keywordsLATERAL
subject keywordsNACA
subject keywordsPOSITION
subject keywordsSIDEWASH
subject keywordsSTABILITY
subject keywordsSTATIC
subject keywordsSURFACE
subject keywordsSURFACES
subject keywordsTAIL
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING
subject keywordsWINGS


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