MAE2_Lecture14

MAE2_Lecture14 - Propulsion II Rocket Engines Rocket...

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Propulsion II Rocket Engines Rocket Equation Staging Spacecraft Maneuvers MAE 2 NASA Image
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2 MAE 2 Rocket Engines A rocket engine does not use air for its combustion process. Fuel and an “oxidizer” are burned in the combustion chamber to yield a high-temperature, high-pressure mixture of gases that expand through a convergent-divergent nozzle. T = ˙ m air ˙ m fuel V e ˙ m air V  p e p A e T = thrust ˙ m air = air mass flow ˙ m fuel = fuel mass flow V e = exit velocity p e = exit static pressure A e = exit area V = freestreamvelocity p = ambient static pressure Thrust Equation: ˙ m = ˙ m fuel ˙ m oxidizer T = ˙ mV e  p e p A e
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3 MAE 2 Exit Velocity Remember the Energy Equation (back in Lecture 3)? c p T 1 1 2 V 1 2 = c p T 2 1 2 V 2 2 c p T 0 = c p T e 1 2 V e 2 c p = specific heat at constant pressure = ratio of specific heats propellants T 0 , p 0 = combustion chamber temperature , pressure
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This note was uploaded on 01/05/2011 for the course MAE 2 taught by Professor Nomura,k during the Fall '08 term at UCSD.

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MAE2_Lecture14 - Propulsion II Rocket Engines Rocket...

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