Maneuver Performance of Fixed-Wing Transport Aircraft

Maneuver performance of fixed-wing transport airplanes is discussed and methods for the analysis of the airplane during turning and pitching maneuvers is presented. General equations are developed for the analysis of the airplane in a level turn, and the factors that can limit the airplane's turn rate are discussed (e.g., available thrust, structural limits and maximum lift coefficient). The angle of attack limit for an airplane is associated with the stall condition, which depends on several factors, such as airplane configuration, weight, load factor and thrust setting. Several safety-critical operational speeds are defined as a fixed multiple of the stall speed. For this purpose, a 1-g reference stall speed is defined. Whereas the stall condition sets a lower speed limit for the airplane, high speed buffet, which is a function of altitude, sets an upper speed limit. The V–n diagram, which depicts the airplane's limit load factor as a function of equivalent airspeed, provides engineers with the basis for determining the structural design loads, and it provides the limits within which the airplane can be safely operated. An outline of the methods used to construct a V–n diagram, as described in the airworthiness regulations, is presented.