Aerospace Engineering > GATE 2012 > Solid Rocket Motors
A solid propellant of density 1800 kg/m3 has a burning rate law r=6.65 x 10-3p0.45mm/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?
Correct : b
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