A solid propellant of density 1800 kg/m3 has a burning rate law r = 6.65 x 10-3

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A solid propellant of density 1800 kg/m3 has a burning rate law r = 6.65 x 10-3p0.45 mm/s, where p is pressure in Pascals. It is used in a rocket motor with a tubular grain with an initial burning area of 0.314 m2. The characteristic velocity is 1450 m/s. What should be the nozzle throat diameter to achieve an equilibrium chamber pressure of 50 bar at the end of the ignition transient?

Options:

A . 35 mm

B . 38 mm

C . 41 mm

D . 45 mm

Answer: Option B

-NA-

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