AlphaCharlie
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Hey there everyone, long time lurker but first time poster, with a question. I've been studying for an upcoming exam and I came across this question in my textbook and I'm absolutely stumped. Any advice would be much appreciated.
An aircraft has a weight of 90,500 N, an aspect ratio of 5.5, a zero lift drag coefficient of 0.031, an Oswald efficiency factor of 0.87, and a wing area of 40 square metres. The aircraft is powered by two jet engines with 32,200 N of static thrust each at sea level. The fuel capacity is 1,675 gallons, the thrust specific fuel consumption is 1 N of fuel per Newton of thrust per hour, and the maximum gross weight is 130,500 N.
Calculate the range and endurance of the aircraft at a standard altitude of 8 km.
An aircraft has a weight of 90,500 N, an aspect ratio of 5.5, a zero lift drag coefficient of 0.031, an Oswald efficiency factor of 0.87, and a wing area of 40 square metres. The aircraft is powered by two jet engines with 32,200 N of static thrust each at sea level. The fuel capacity is 1,675 gallons, the thrust specific fuel consumption is 1 N of fuel per Newton of thrust per hour, and the maximum gross weight is 130,500 N.
Calculate the range and endurance of the aircraft at a standard altitude of 8 km.