Abstract
Nomenclature A e — nozzle exit area A t = nozzle throat area C* = characteristic velocity g = gravitational acceleration / = delivered impulse Isp — specific impulse Isp.d = delivered specific impulse m = propellant mass 777 = nozzle flow rate p = pressure p m = mass averaged pressure p ( = time averaged pressure p r = mean pressure for burning rate p = mean pressure r = burning rate / = time ta = action time tb = burn time /7 =time when p first becomes 0.05 pt w_ = propellant web ( ) = denotes a mean e — nozzle expansion ratio
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