Abstract
A* = nozzle throat area, in. AC = combustion chamber cross-sectional area, in. Ae = nozzle exit plane area, in. F = thrust, Ib h = heat-transfer coefficient, Btu/hr-ft-°R /sp = specific impulse, Ibf/(Ibm/sec) // = total impulse, Ib-sec k = thermal conductivity, Btu/hr-ft-°F L* = characteristic length, in. Pc = chamber pressure, psia P i nj = propellant injection pressure, psia q/A = heat flux, Btu/hr-ft TI = inside radius, in., ft Tg = gas recovery temperature, °R Tw = wall temperature, °R T co = effective heat sink temperature, °R t — wall thickness, in. AT = temperature difference between gas and wall V = velocity, fps WfC — coolant flow WT = propellant plus coolant flow, Ib/sec 6 = time, sec e = exterior wall emissivity a = effective thermal diffusivity, in./sec 5 = char depth, in. a= Stefan-Boltzmann constant, Btu/ft-°R-hr
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