This invention discloses a rapid calculation method for the rearward
infrared radiation intensity of an S-curve
nozzle, belonging to the field of
infrared radiation characteristic
simulation of aero-engine exhaust systems. The method comprises the following steps: determining the design parameters of the S-curve
nozzle and exhaust mixer components; establishing projection models of the key shielding sections of the exhaust mixer and S-curve
nozzle; calculating the
projected area of each component after shielding by the S-curve nozzle using an image method; calculating the flow field
parameter distribution and component surface temperature of the S-curve nozzle; calculating the
axial length and volume of the visible region of the
exhaust gas in the S-curve nozzle; calculating the
spectral transmittance and spectral
radiance of the
exhaust gas along the nozzle outlet centerline within the visible region of the
exhaust gas, as well as the spectral
radiance intensity of the exhaust gas; calculating the
infrared spectral
radiance intensity of the wall surface; and integrating the spectral radiance to obtain the total infrared
radiation intensity. This method solves the problems of existing technologies where the
simulation calculation of the infrared radiation characteristics of S-curve nozzles is complex and time-consuming, and rapid
calculation methods are only applicable to axisymmetric nozzles and cannot simulate the shielding structural characteristics of S-curve nozzles.