The burning rate of a particular propellant is given by r=c/(T₁−T) p₀ⁿ in which r is in mm/s, p₀ is in MPa, T is in K and
c = 176,
T₁ = 415 K,
n = 0.716.
When the propellant initial temperature is 20⁰ C, the chamber pressure is 3MPa (steady) for 4 min. If the same propellant grain in the same rocket is heated to 45⁰ C, what would be the new steady state pressure level and burning period. Assume the time required to reach steady state is small compared to the burning time.