关键词: 组合发动机；蒙皮壁温；气动加热；辐射传热；发射率；攻角

Abstract: In order to meet the demand of the thermal protection for a combined-cycle engine，the aerodynamic heating and radiative heat transfer of the combined-cycle engine were calculated by reference temperature approach and atmospheric transmittance calculation soft MODTRAN4，respectively. The one dimensional steady state temperature distribution of the combined-cycle engine skin under some typical flight operation conditions was obtained by iterative computating the equation of steady state heat balance. Comparison between the calculated results and the experiment results conducted by NASA shows that the error was less than 6%. A series of studies with different skin emissivities，different angles of attack under some typical flight operation conditions were carried out. The results show that，the skin temperature decreases with the growing emissivity and increases with the growing angle of attack. Under a typical flight operation condition，the skin temperature decreases by 98.01K，a decline of 12.76% ，when the skin emissivity varies from 0.1 to 1.0，and the skin temperature increases by 95.45K，a rise of 13.14% ，when the angle of attack varies from 0° to 45°.

Key words: Combined-cycle engine；Skin temperature；Aerodynamic heating；Radiative heat transfer；Emissivity；Angles of attack