$MW=29k\frac{g}{k}w$

The Following Performance and operation data was obtained from a

rocket with a a nozzle designed to produce maximum thrust at sea

level:

Determine;

A$)$ Specific Impulse

B$)$ Mass Flow Rate

C$)$ Furoat Diameter

D$)$ Exit Diameter

E$)$ Thrust Produced at An altitude of $30$ KM for the same fixed Nozzle

Geometry