A rocket engine is designed to operate isentropically $($critical condition $3)$ at $10,000$ m with a chamber pressure of $2000$ kPa and a chamber temperature of $2800$ K$.$ The products of combustion behave as a perfect gas with $=1\mathrm{.}35$ and MW $=20$ kg$/$kg$-$mol. Determine the thrust of the engine if the throat area is $0\mathrm{.}10$ m$2.$ The United States Standard Atmosphere $1976$ provides accepted physical properties as a function of altitude. A rocket engine is designed to operate isentropically $($critical condition $3)$ at $10,000m$

with a chamber pressure of $2000$ kPa and a chamber temperature of $2800$ K $.$ The

products of combustion behave as a perfect gas with $=1\mathrm{.}35$ and $MW=20k\frac{g}{k}g-$mol.

Determine the thrust of the engine if the throat area is $0\mathrm{.}10m^2.$ The United States

Standard Atmosphere $1976$ provides accepted physical properties as a function of

altitude.