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

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 specific fuel consumption on Mach number. It is also proved that the classical analytical approach assuming constant specific fuel consumption and uncambered wing drag polar results in higher optimum Mach numbers and shorter ranges for constant-altitude-constant-airspeed ight of turbojet/fan transport aircraft.