Computing Method Investigation and Verification of Gas-Solid Combustion in Magnesium-Aluminum Based Propellant Ducted Rocket

摘要

The combustion mechanism,which consisting of 22 species and 23 reaction equations,and three discrete models such as inertia,combusting,modification droplet,are employed for the investigation of gas-solid combustion in magnesium-aluminum based propellant ducted rocket based on thermal performance calculation.And path lines,temperature distribution,sediments are discussed after the computing method is validated by direct-connect experimentation and the flow field information,which obtained by numerical method and coincided with currently conclusions.The results indicated that the proposed method is reliable and practicable.