MAE2_Lecture14

# MAE2_Lecture14 - Propulsion II Rocket Engines Rocket...

This preview shows pages 1–4. Sign up to view the full content.

Propulsion II Rocket Engines Rocket Equation Staging Spacecraft Maneuvers MAE 2 NASA Image

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
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
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

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
This is the end of the preview. Sign up to access the rest of the document.

{[ snackBarMessage ]}

### Page1 / 8

MAE2_Lecture14 - Propulsion II Rocket Engines Rocket...

This preview shows document pages 1 - 4. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online