Calculating Aircraft Range and Endurance Using De Breguet Formula

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SUMMARY

The discussion centers on calculating the range and endurance of an aircraft using the De Breguet formula. Key parameters include an aircraft weight of 90,500 N, a wing area of 40 square meters, and a thrust specific fuel consumption of 1 N per hour per thrust. The calculations require the aspect ratio of 5.5, a zero lift drag coefficient of 0.031, and an Oswald efficiency factor of 0.87. The aircraft is powered by two jet engines, each providing 32,200 N of thrust, and has a fuel capacity of 1,675 gallons.

PREREQUISITES
  • Understanding of the De Breguet formula for aircraft range and endurance
  • Knowledge of aerodynamic principles, including drag coefficients and aspect ratios
  • Familiarity with thrust specific fuel consumption metrics
  • Basic calculations involving weight and fuel capacity in aviation contexts
NEXT STEPS
  • Study the De Breguet formula in detail to understand its application in various flight scenarios
  • Learn about the impact of altitude on aircraft performance and fuel efficiency
  • Research the effects of different thrust specific fuel consumption rates on range calculations
  • Explore case studies of aircraft performance calculations using real-world data
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Aerospace engineering students, aviation professionals, and anyone involved in aircraft performance analysis will benefit from this discussion.

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.
 
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Use the De Breguet formula.
 

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