The flow field and the wall temperature distribution calculation models on a converging-diverging nozzle considering the heat conduction

heat convection and radiation heat transfer are established and computed.The flow field is governed by the Navier-Stokes equations and the equations are solved based on the density solver.The wall temperature distribution calculation model is based on the heat transfer mechanism and the heat flux equilibrium.And the corresponding FORTRANprograms for the three layer wall temperature calculation of the nozzle are written.Many flight cases are calculated in which the properties of the burning gas mixture are calculated by a series of formulas and methods considering them varied with the pressure

the temperature and the ratio of oil to air.The results show that the heat shield temperature and the converging-diverging nozzle cylindrical wall temperature increase along the flow direction and decrease in the expand segment of the nozzle.The maximum wall temperature happens around the nozzle throat position.The outer adjustment plate temperature outside of the nozzle cylinder reaches its maximum some little before the nozzle throat position.The best agreement between the calculation and the given data can be observed in the paper.