Linearized equations of motion of rolling bisymmetric aircraft formulated, using body axes; it is shown that (a) rate of change of angle of attack is vector, (b) linearized form of downwash lag terms is valid only if downwash-roll angle be small, and (c) such linearized form must use vector relations of (a); as result, stability criteria are derived independent of rolling of reference axis system.
Response of bisymmetric aircraft to small combined pitch, yaw, and roll control actions
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 24 , n 12
1957
6 pages
Article (Journal)
English
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