Power optimization of a single propeller airplane take-off run on the basis of lateral maneuver limitations

The problem of selecting optimal take-off run power of a single propeller airplane on the basis of the lateral maneuver limitations is analyzed in this paper. The single propeller reactive torque as the function of engine power and speed generates non-aerodynamic asymmetric load disturbance. The capability of lateral flight control surfaces to compensate for this asymmetric load and perform the required maneuver defines the safe flight envelope boundaries in the form of engine power setting - airspeed relation. The take-off run length consisting of acceleration, decision making, brake activation and airplane stopping length distances is calculated for engine power settings along the safe flight boundaries defined by the lateral flight control capabilities. The minimum of take-off run along thus defined safe flight boundary determines the engine optimal power setting. The results are presented for the example of the single propeller airplane on concrete runway surface.