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NACA-TN-1423

The stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:12:47Z
date available2017-09-04T16:12:47Z
date copyright01/01/1947
date issued1947
identifier otherSPTSYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/76046
description abstractThe stability derivatives treated herein are listed, together with the values found for then, in table I. The derivations that follow give the values with reference to the principal body axes of figure 1 with origin at the aerodynamic center (2/3c, 0, 0). Conversion has been made to the system of stability axes shown in figure 3 with origin a distance xcg ahead of the 2/3c point (transformation equations in reference 3). Table I comprises parallel columns which present the values relative to both systems.
languageEnglish
titleNACA-TN-1423num
titleThe stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speedsen
typestandard
page36
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAIR
subject keywordsAIRFOILS
subject keywordsASPECT
subject keywordsCALCULATIONS
subject keywordsDELTA
subject keywordsDIHEDRAL
subject keywordsDISTRIBUTION
subject keywordsFLOW
subject keywordsFUSELAGES
subject keywordsHIGH
subject keywordsINTERFERENCE
subject keywordsPRESSURE
subject keywordsRATIO
subject keywordsSIDESLIPPING
subject keywordsSMALL
subject keywordsSTABILITY
subject keywordsSUBSONIC
subject keywordsSUPERSONIC
subject keywordsTHIN
subject keywordsVELOCITY
subject keywordsWINGS


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