The invention discloses a
rocket plume
simulation method which includes the following steps that an unstructured grid is generated by means of Gambit
software and a boundary condition is set; the grid is led into Fluent, and plume flow field physical models are solved by means of Fluent
software, wherein the plume flow field physical models include a turbulence model, a dispersed
phase model and a
combustion model; a boundary condition and an iteration initial value are set in the Fluent according to model requirements or actual situations, and flow
field data are obtained through analog
simulation. a parameter model for plume flow field compute is built based on the mechanism study of a
rocket plume flow field and according to the
combustion theory, hydromechanics and
gas dynamics and with the consideration of
combustion chemical reactions in a
combustion chamber, main features of the plume flow field can be objectively described, flow
field data on specific conditions are quickly obtained through
simulation, input parameters are provided for compute of
infrared features of
rocket plumes, plume computer precision is improved, and plume simulation time is saved.