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Unformatted text preview: Question 9: The data below describes a large, solid fuel rocket similar to the two booster rockets used for the space shuttle. From the information given, estimate a) the gas exit velocity and thrust force produced at sea level where P atm = 100 kPa (i.e. thrust at lift-o). b) the total mass that this rocket could accelerate vertically with acceleration g, ignoring air drag. Propellant mass = 500,000 kg; burn time = 130 s; combustion temperature = 3000 C . Assume constant m versus time during the burn. Nozzle throat diameter = 1.15 m; exit diameter = 3.5 m. The fuel is mainly ammonium perchlorate and aluminium is a polymer binder. Assume the exhaust is an isentropic perfect gas ow with k = 1.4 and R is unknown (i.e. not air)....
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This note was uploaded on 09/14/2011 for the course ME 362 taught by Professor Ceciledevaud during the Winter '11 term at Waterloo.
- Winter '11