Series of simple theoretical models are discussed, representing features of flexible aircraft of classical and integrated varieties, in trimmed level flight; maximum speed for trimmed flight for classical aircraft is determined primarily by tail plane flexibility; for integrated aircraft maximum speed occurs when both overall aeroelastic distortion and control forces become very large, effectiveness of control to trim is related to similarity of weight and aerodynamic lifting distributions; aeroelastic effects of trimmed plate wings in level flight are also investigated.
Some static aeroelastic considerations of slender aircraft
AGARD -- Report
1961
17 pages
Report
English
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