Unformatted text preview: thrust-to-weight ( T/W) ratio. This is an open ended home work. The accuracy of the numbers is not important, but you need to 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. Given the drag polar of the airplane being , determine the thrust required to sustain this flight. (Relevant atmospheric data can be found in the text book)...
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- Spring '08
- Aerodynamics, Fixed-wing aircraft, Wing, Program Outcomes a-k