The dependence of radar attenuation on exhaust gas temperature has been previously used both as a semiempirical correlative technique and as a means of identi fying the dominant electron source. A method is presented of relating this observed temperature dependence to fundamental propulsion system characteristics in both the equilibrium and nonequilibrium flow regimes. Implications of the theory are discussed and illustrative calculations are given for a class of conical expansion section, onedimensional nozzle flows. Results are compared with attenuation measurements recently reported on aluminized solid propellant motors. (Author)
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