Range and Endurance of Jet-Engined Airplanes at Constant Altitude

摘要

The cruise performance of turbojet and turbofan engined airplanes flying at constant altitude is studied. The drag polar is assumed parabolic and independent of Mach number. The fuel consumption is assumed to be a linear function of net thrust (i.e., a constant plus a second constant times thrust). Formulas for range and endurance are presented for three different cruising techniques: flight at optimum instantaneous velocity, flight at constant angle of attack, and flight at constant velocity. Approximate formulas for optimum velocities (maximizing range and endurance) are derived.