A LOX$/$LH$2$ bipropellant rocket engine used for launch vehicle upper stages has nozzle throat diameter of $0\mathrm{.}132$ m and exit diameter of $2\mathrm{.}235$ m $.$ In vacuum, the engine produces $110$ kN of thrust with specific impulse of $460$ s $.$ Assume the average molecular weight and specific heat ratio of the prope

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.llant are equal to $10k\frac{g}{k}$mol and $1\mathrm{.}26,$ respectively.