Constant Altitude–Constant Mach Number Cruise Range of Transport Aircraft with Compressibility Effects

An approximate solution of the constant altitude–constant Mach number cruise range for high subsonic speed flight of the turbojet/fan aircraft is proposed. The solution considers cambered wing drag polar of modern transport aircraft, dependence of the specific fuel consumption on Mach number, and compressibility effects on aerodynamic characteristics of the aircraft. The method aims for a quick assessment of the cruise range during conceptual or preliminary design phase. An application of the method to a known type of aircraft is also presented.