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NASA-TN-D-8391

Calculations, and comparison with an ideal minimum, of trimmed drag for conventional and canard configurations having various levels of static stability

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:51:36Z
date available2017-09-04T16:51:36Z
date copyright01/01/1977
date issued1977
identifier otherWQYKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/115193
description abstractClassical drag equations were used to calculate total and induced drag and ratios of stabilizer lift to wing lift for a variety of conventional and canard configurations. The Flight efficiencies of such configurations that are trimmed in pitch and have various values of static margin are evaluated. Classical calculation methods are compared with more modern lifting surface theory.
languageEnglish
titleNASA-TN-D-8391num
titleCalculations, and comparison with an ideal minimum, of trimmed drag for conventional and canard configurations having various levels of static stabilityen
typestandard
page25
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1977
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsCANARD
subject keywordsCONFIGURATIONS
subject keywordsDEVICES
subject keywordsDRAG
subject keywordsINDUCED
subject keywordsLIFT
subject keywordsMEASUREMENT
subject keywordsRATIO
subject keywordsSTABILITY
subject keywordsSTATIC
subject keywordsSTRUCTURES
subject keywordsTANDEM
subject keywordsWING


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