Experimental validation of flow field in the secondary combustor of a subscale ducted rocket

Experimental validation method through temperature field measuring in the secondary combustor of ducted rocket was developed. A subscale ducted rocket motor and a thermo-rake were designed. Direct connection experiments were carried out using low combustion temperature solid propellant products as primary flow and air as secondary flow. The mass flow rate and pressure of air and hot gas at the entrance of secondary combustor were calculated based on the measured pressure and structural parameters, and were used as boundary condition in numerical simulation. The experimental results agree to a certain extent with the numerical simulation and it indicates that this validation method is effective, and the numerical simulation method is also effective.