Q3)\ A LOX/LH2 bipropellant rocket engine used for launch vehicle upper stages has nozzle throat diameter of

0.132m

and exit diameter of

2.235m

. In vacuum, the engine produces

110kN

of thrust with specific impulse of

460s

. Assume the average molecular weight and specific heat ratio of the propellant are equal to

10k(g)/(k)mol

and 1.26 , respectively.\ a) Calculate the effective exhaust sped.\ b) Determine the propellant mass flow rate.\ c) Determine the Mach number at nozzle exit.\ d) Determine the thrust coefficient in vacuum.\ For the engine given in question , estimate the following parameters:\ a) Chamber pressure and temperature,\ b) Nozzle throat pressure and temperature, and\ c) Nozzle exit pressure and temperature.\ For the engine given in question , assuming no change in chamber pressure and temperature with altitude, determine the following parameters at the design altitude of the engine:\ a) Thrust,\ b) Thrust coefficient, and\ c) Specific impulse.

A LOX/LH2 bipropellant rocket engine used for launch vehicle upper stages has nozzle throat diameter of 0.132m and exit diameter of 2.235m. In vacuum, the engine produces 110kN of thrust with specific impulse of 460s. Assume the average molecular weight and specific heat ratio of the propellant are equal to 10kg/kmol and 1.26 , respectively. a) Calculate the effective exhaust sped. b) Determine the propellant mass flow rate. c) Determine the Mach number at nozzle exit. d) Determine the thrust coefficient in vacuum. For the enginie given in question , estimate the following parameters: a) Chamber pressure and temperature, b) Nozzle throat pressure and temperature, and c) Nozzle exit pressure and temperature. For the engine given in question , assuming no change in chamber pressure and temperature with altitude, determine the following parameters at the design altitude of the engine: a) Thrust, b) Thrust coefficient, and c) Specific impulse