For an ideal rocket with a characteristic velocity c of 1220

For an ideal rocket with a characteristic velocity c* of 1220 m/sec, a mass flow rale of 73.0 kg/sec. a thrust coefficient of 1.50, and a nozzle throat area of 0.0248 m^2. compute the effective exhaust velocity, the thrust, the chamber pressure, and the specific impulse.

Solution

1) effective exhaust velocity = thrust coefficient * charactristic velocity

= 1.5 * 1220

= 1830 m/sec

2) Thrust = mass flow rate * effective exhaust velocity

= 1830* 73

= 133590 N

3) The chamber pressure = (characteristic velocity* mass flow rate)/Area

= (1220*73)/0.0248

= 3591129.032 N/m^2

= 3.59*10^6 N/m^2

4) Specific impulse = effective exhaust velocity/acceleration due to gravity(g)

= 1830/9.81

= 186.7 sec