Figure $4\mathrm{.}31$ Diagram for Problem $4\mathrm{.}39.$Average chamber pressure $=860$

Propellant consumption $=6400lb$

Burning duration $=110s$

Determine the following quantities from these data:

$($a$)$ average specific impulse;

$($b$)$ propellant characteristic velocity;

$($c$)$ average thrust coefficient;

$($d$)$ vacuum specific impulse;

$($e$)$ chamber temperature, assuming $M=20l\frac{b}{l}b-$mol; and

$($f$)$ overall efficiency $-$ this is the ratio of the measured and ideal thrust values

$($You may assume $=1\mathrm{.}2$ in all calculations.$)$

The Answers Are Approximately $309$s$,5980$ ft$/$s$,1\mathrm{.}666,312$s$,6050$ R$,91\%$