Abstract: Two different approximate solutions are proposed and compared with the numerical solution of the constant altitude - constant Mach number cruise range for turbojet/fan aircraft.

• 文章摘要: 给出了涡喷／涡扇飞机定高定速巡航段航程的两种估算方法，考虑了机翼弯度和耗油率变化的因素，并进行了数值计算。