Approximate solutions of range for constant altitude – constant high subsonic speed flight of transport aircraft

Approximate cruise range solutions are introduced for the constant altitude – constant high subsonic speed flight of turbojet/fan transport aircraft with cambered wing design. The variation of the specific fuel consumption with Mach number is also considered in derivation of the approximate solutions. The method aims at estimation of the cruise range of aircraft during conceptual or preliminary design phase. An application of the solutions is also presented.