Abstract
Numerical simulations are carried out to evaluate the nozzle damping of rocket motors. A subscale cold flow experimental condition where nozzle damping coefficients are evaluated through the pulse decay method is taken as a validation case. The flowfield of the motor is simulated by solving three-dimensional Reynolds-averaged Navier–Stokes equations using commercial computational fluid dynamics software. The trend of the pressure decay in the head end is well captured for different values of port-to-throat area ratios, and a very good match is obtained between the computed and experimental values of the nozzle decay coefficient. Validated methodology is used to evaluate the damping coefficient of a burning solid rocket motor with composite propellant.
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