Modeling Acceleration Effects on Ram Accelerator Thrust at High Pressure

Abstract

A = tube section a = acceleration cp = isobaric heat capacity F = thrust h = specific enthalpy I = nondimensional thrust, F/(p A) L = length M = Mach number m = mass P = pressure ratio p = pressure Q = nondimensional heat release, q/cpT R = gas constant T = temperature u = velocity v = specific volume α = intermediate calculation parameter, LCVap = adiabatic specific heat capacity ratio γ = specific heat capacity ratio q = heat release η = calorific imperfection, h/cpT σ = compressibility factor