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MEM425F10.HW1 - thrust-to-weight T/W ratio This is an open...

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MEM 425: Aircraft Performance & Design Home work #1 (due 09/30/10) Relevance to Program Outcomes a-k : a, k Problem I: 1. Identify any two airplanes (fixed wing, not rotary) that pick your interest. Explain what makes them interesting and what you think are its implications. 2. Tabulate all relevant data you collect on these aircrafts; geometry, weight, aerodynamics, propulsion, etc. Use technical terms as appropriate, such as wing-span, aspect ratio,… 3. Roughly estimate the coefficients of Lift and Drag while in cruise based on the data available for these aircraft. Also estimate the wing loading (weight-to-wing_area, W/S ratio) and the
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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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