The maximum endurance is obtained at a flight condition that results in the lowest fuel flow rate or minimum fuel consumption. The basic theory is simple: for constant SFC the fuel flow rate (G) is directly proportional to power required and therefore the
Fig. 3.8 Flight conditions required for optimum range performance (5500 kg).
RANGE PERFORMANCE (VIP)
Fig. 3.9 Achievable range performance.
true airspeed for maximum endurance (VME) occurs at the speed for minimum power, see Fig. 3.10.