You are testing a

H_(2)-O_(2)

rocket engine at an experimental and highly classified test facility. The

H_(2)-O_(2)

reaction occurs stoichiometrically (producing water) at a chamber stagnation pressure of

2.0MPa

. A nozzle, with an area ratio of 42.26 , has been attached to the combustion chamber and the engine fired on a testing platform. The nozzle is designed for optimal isentropic expansion at the altitude of the test facility. Testing determines that the static exit temperature is

1700K

. Furthermore, the engine produces

445kN

of thrust. Assume

\\\\gamma =1.19

.\ Determine the following:\ a. The chamber stagnation temperature\ b. The specific impulse of the engine\ c. The mass flow rate of propellant required\ d. The diameter of the nozzle throat\ e. The ambient pressure at the test facility\ f. The approximate (to the nearest

1000m

) altitude of this test facility

You are testing a H2O2 rocket engine at an experimental and highly classified test facility. The H2O2 reaction occurs stoichiometrically (producing water) at a chamber stagnation pressure of 2.0MPa. A nozzle, with an area ratio of 42.26 , has been attached to the combustion chamber and the engine fired on a testing platform. The nozzle is designed for optimal isentropic expansion at the altitude of the test facility. Testing determines that the static exit temperature is 1700K. Furthermore, the engine produces 445kN of thrust. Assume =1.19. Determine the following: a. The chamber stagnation temperature b. The specific impulse of the engine c. The mass flow rate of propellant required d. The diameter of the nozzle throat e. The ambient pressure at the test facility f. The approximate (to the nearest 1000m ) altitude of this test facility