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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 Fall '08
 Nomura,K
 Aerodynamics, Spacecraft propulsion, 7g, 4.1g, final burnout velocity, exit gas velocity

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