Unformatted text preview: explain clearly how you determined them. Include reference to the source for your information. Problem II: An airplane weighing 20,000 lb, is in a cruise flight (constant altitude, constant velocity, level flight) at an altitude of 20,000 ft, with a velocity of 0.6 Mach. Its wing area is 1000 ft 2 . Given the drag polar of the airplane being , determine the thrust required to sustain this flight. Hint : find lift, coefficient of lift, coefficient of drag, drag, and the thrust.(Relevant atmospheric data can be found in the text book) Relevance to Program Outcomes a-k : a, k...
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- Fall '08
- Aerodynamics, Fixed-wing aircraft, Program Outcomes a-k, open ended home