Comparison of Generalized Approximate Cruise Range Solutions for Turbojet/Fan Aircraft

Abstract

Two different approximate solutions are proposed and compared with the numerical solution of the constantaltitude‐ constant-Mach-number cruise range for turbojet/fan aircraft. The approximate solutions consider both cambered wing drag polar and dependence of specie c fuel consumption on Mach number. It is also proved that the classical analytical approach assuming constant specie c fuel consumption and uncambered wing drag polar results in higher optimum Mach numbers and shorter ranges for constant-altitude‐ constant-airspeed e ight of turbojet/fan transport aircraft.