Abstract
Abstract This chapter deals with the static lateral stability and trim conditions for a fixed‐wing aircraft having a conventional geometry (wing, horizontal, and vertical tail plane). The aircraft is considered as a rigid body. The basic control systems are shown for a conventional vehicle consisting of a wing with aileron, a horizontal tail with elevator, and a vertical tail with rudder. The simple case of a banked turn is presented.Then the pitching moment equations are derived for the wing alone and the full aircraft. Two particular cases are considered: (i) minimum control speed in air for a flight with asymmetric thrust; (ii) aircraft in straight rolling motion without inertia coupling.The lateral stability conditions in roll are derived and the main parametric effects are discussed.
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