Abstract
AUSM arithmetic and King boron particle combustion model have been efficiently implemented to numerical investigate integrated combustion chamber and inlet for variable flow ducted rocket. The effect of the ducted rocket performance from increscent gas flow was investigated. Numerical results indicated that the increase of gas flow reduced performance of ducted rocket with fixed inlet. The rocket thrust is enhanced, yet special impulse descends and flight of missile is reduced. In order to improve the performance, several importance factors, such as flight trajectory and air flux should be calculated synthetically and inlet design point should be selected and optimized reasonably for inlet design of variable flow ducted rocket.
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