MAE2_Homework5

MAE2_Homework5 - The payload mass is 60 kg and the specific...

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MAE 2 Homework #5 (Fall 2010) Note: Some numbers and wording may be changed relative to the textbook problems. When differences occur, this assignment sheet has precedence. Problem 9.4 Calculate the engine thrust of a turbojet-powered airplane flying at a standard altitude of 40,000 ft and velocity of 530 mi/hr. The engine inlet area is 13 ft 2 and the exit area is 10 ft 2 . The exit gas velocity and pressure are 1500 ft/s and 450 lb/ft 2 , respectively. Problem 9.11 A rocket, using hydrogen-oxygen as the fuel-oxidizer combination, has a specific impulse of 360 sec. Calculate the ratio of the propellent mass to the initial mass required to achieve a burnout velocity equal to the escape velocity from Earth. Problem 9.13 Calculate the final burnout velocity for the following two-stage rocket.
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Unformatted text preview: The payload mass is 60 kg and the specific impulse for both stages is 275 sec. 1st Stage: propellent mass = 7200 kg, structual mass = 800 kg 2nd Stage: propellent mass = 5400 kg, structural mass = 600 kg Problem S1 An aerobatic airplane has a wing loading of W/S = 60 lb/ft 2 and a maximum lift coefficient of CLmax = 1.5. Will the aircraft exceed its 7g structural load factor limit if it performs a 25 deg/sec level turn at sea level? Problem S2 Compute and plot the elliptical lift distribution, as a function of spanwise location, for an airplane wing that is operating at a +4.1g load factor. The airplane weighs 15,700 lb and its wingspan is 269 ft....
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This note was uploaded on 02/01/2011 for the course MAE 2 taught by Professor Nomura,k during the Fall '08 term at UCSD.

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