飞行器8~14μm波段红外特征的数值研究

在飞行器机身表面的温度场建模中综合考虑了超音速飞行气动加热、发动机舱内部流动换热，以及排气喷流对飞行器后体的传热等影响， 采用数值计算的方法对飞行器8~14m波段的蒙皮及发动机壁面红外辐射特征进行了研究，分析了飞行器机头、机身（含进气道）、机翼、发动机舱（含飞行器后体）、垂直尾翼、水平尾翼和发动机喷管腔体等部位的红外辐射。结果表明:蒙皮辐射是飞行器8~14m波段红外辐射的主要组成部分，发动机壁面红外辐射主要集中在飞行器尾向50范围内；在不同的观测平面，飞行器不同部位对整机8~14m波段的红外辐射贡献比例各有侧重，飞行器机身、机翼、发动机舱和垂直尾翼是飞行器8~14m波段红外辐射的主要部分；飞行马赫数提高将加剧机身气动加热效果，飞行机不同部位所占的红外辐射比例将有所改变。

Numerical investigation of aircraft infrared characteristics in 8-14 μm band

Practical ways of modeling aerodynamic heating under supersonic flight conditions, flow and heat transfer inside aero-engine nacelle, and plume heating on the rear fuselage of aircraft were introduced for simulating the aircraft skin temperature distributions. Infrared radiation characteristics in 8-14 m band of skin and engine wall was studied by numerical calculation method. Contribution of head, fuselage (including inlet entrance), wing, engine compartment (including rear fuselage), vertical stabilizer, horizontal stabilizer and engine nozzle cavity to infrared radiation were analyzed. The results show that skin infrared radiation is the major component of the infrared radiation in 8-14 m band and the infrared radiation of the engine wall is mainly focused on the aircraft tail in the visual range of 50. The individual infrared radiation of skin compartment takes different proportion of total infrared radiation in different observation plane. The main sources of infrared radiation are aircraft body, wing, aero- engine nacelle and upward vertical tail. Aerodynamic heating effect is exacerbated with the rising of flight Mach number, as a result of which proportion of each part of the aircraft infrared radiation changed.