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NASA-CR-176615

Exploratory low-speed wind-tunnel study of concepts designed to improve aircraft stability and control at high angles of attack

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:57:30Z
date available2017-09-04T15:57:30Z
date copyright01/01/1985
date issued1985
identifier otherRANKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/60790
description abstractA wind tunnel investigation of concepts to improve the high angle-of-attack stability and control characteristics of a high performance aircraft was conducted. The effect of vertical tail geometry on stability and the effectiveness of several conventional and unusual control concepts was determined. These results were obtained over a large angle-of-attack range. Vertical tail location, cant angle and leading edge sweep could influence both longitudinal and lateral-directional stability. The control concepts tested were found to be effective and to provide control into the post stall angle-of-attack region.
languageEnglish
titleNASA-CR-176615num
titleExploratory low-speed wind-tunnel study of concepts designed to improve aircraft stability and control at high angles of attacken
typestandard
page73
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1985
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsANGLE
subject keywordsASSEMBLIES
subject keywordsATTACK
subject keywordsCHARACTERISTICS
subject keywordsDYNAMICS
subject keywordsEDGE
subject keywordsFLUID
subject keywordsLEADING
subject keywordsSTABILIZERS
subject keywordsSTALLING
subject keywordsSUPERSONIC
subject keywordsSWEEP
subject keywordsTAIL
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND


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