Abstract
The use of matrices facilitates the solution of the spanwise lift distribution for the case of a flexible wing for all conditions of load factor, incompressible air speed, aileron and flap deflection, and roll in a convenient form within the range of linear variation |of section lift with angle of attack. The method yields the critical values of wing divergence speed, aileron reversal speed, and wingaileron divergence speed, without additional computational effort, for the conventional wing and may be adapted to the sweptback wing.
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