Abstract
ao = freestream speed of sound cp = specific heat at constant pressure gc = Newton’s constant hPR = fuel lower heating value Mo = Mach number at freestream conditions M o = freestream Mach number for minimum S S = thrust-specific fuel consumption T = temperature Tmax = material temperature limit To = freestream temperature Tto = freestream total temperature = ratio of specific heats b = = r r = inlet temperature ratio, Tto=To 1 1 M o=2 = material temperature limit to freestream temperature ratio, Tmax=To
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