Models of heat shield and inner

outer shells were built for investigation.A coupled simulation method of gas radiation and nozzle wall temperature was established based on neat radiation in an enclosure model and heat balance model of wall.Gas radiation in 1~5μm was computed with narrow band model

which was considered transparent in all other bands.A coupled equation of neat radiative heat flux-effective radiosity-wall temperature was developed

and the Newton Rafael method was used to solve the heat balance equation to obtain wall temperature of nozzle.An axisymmetric vectored nozzle with 20°deflection angle was taken for investigation.The infrared spectral radiation and neat radiative heat flux on the nozzle wall and the wall temperature were computed.For verification of the computation method

the neat radiative heat flux for one axisymmetric nozzle of a liquid rocket motor were computed

showing well agreement through comparison. This study also shows that radiative heat flux and temperature in deflected section of axisymmetric vectored nozzle varies remarkably along the circumferential direction

much lower on the deflecting side than the other side.Wall temperature of deflecting side is about 90% of the other side

while the radiative heat flux is only 50%.