Combustion of aluminum particles in solid rocket motor flows

Nomenclature B Spalding transfer number of fuel mass fraction CD = drag coefficient Cmix = total molar concentration, mol/cm D = droplet diameter, /xm DO = initial droplet diameter, /xm D/ = fuel diffusion coefficient, cm/s ^ox-mix = oxidizer diffusion coefficient, cm/s (g) = gas-phase [i ] = molar concentration of species i, mol/cm k = burning rate coefficient, //,m//xs ki = reaction rate for oxidizer /, cm/mol-s (/) = liquid-phase Lc = thermal diffusion layer thickness, /xm ^diff-ox = ft^ diffusive flux, mol/cm-s n = D exponent p = pressure, atm ReD = Reynolds number r/rs = nondimensional radius referenced to droplet surface r' propellant burning rate, cm/s t = time, IJLS tb = burn time, /xs Xeff = oxidizer concentration expressed as a mole fraction Xi = oxidizer concentration of species /

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