In the analysis of aircraft dynamics far up and13; away flight, the general practice consists of trimming13; the aircraft for a specific maneuvers at a specified13; Altitude and Mach number. In this paper conditions for13; Quasi-steady equilibrium are motivated for aircraft13; dynamics in the ground roll phase. Algorithms for13; implementation of these conditions are also described.13; By use of these algorithms, the locus of trim points is13; obtained for a comprehensive take-off maneuvers of a13; delta wing aircraft beginning with ground roll,13; followed by rotation and ending in lift-off. This result13; is compared with approximate calculations wherein the13; landing gear states are ignored and linear13; aerodynamics is assumed. The exact result is also13; compared with the simulation of the take-off13; maneuvers in a pilot in the loop simulator.13
