【摘要】 为了研究发动机排气系统向飞机后体传热而对飞机红外辐射特征产生的影响，建立了考虑和不考虑排气系统与飞机后体传热组合模型，通过有限体积法和反向蒙特卡罗法分别计算2种模型的流动传热特性和红外辐射特性。结果表明：考虑排气系统与飞机后体传热时，在竖直探测面上，3～5μm波段积分辐射强度在探测角α=55°时增幅最大，增加了2.97%;8～14μm波段积分辐射强度在α=40°时增幅最大，增加了8.9%;3～5μm波段积分辐射强度随着探测角增大而先提高后降低，在α=5°时最高；8～14μm波段积分辐射强度随着探测角增大而先提高后降低，在α=90°时最高；飞机表面发射率由0.9降低到0.1时，在水平探测面上，α=45°，8～14μm积分辐射强度降低了78.6%，但是3～5μm波段积分辐射强度并没有降低，反而提高了2.56%。更多还原

【Abstract】 To investigate the influence of heat transfer from the engine exhaust system to the aircraft afterbody on aircraft infrared radiation signatures, aircraft-engine exhaust system integrated models considering and not considering the heat transfer effect were established. The flow and heat transfer characteristics and infrared radiation characteristics of the two models were calculated using the finite volume method and reverse Monte Carlo method,respectively.The results show that when the heat transfer between the exhaust system and the aircraft afterbody is considered,on the vertical detection plane,the integrated radiation intensity peaks at α(detection angle)=55 ° in the 3～5μm band,an increase of 2.97%,while the intensity peaks at α=40 ° in the 8～14μm band,an increases of 8.9%.In the 3-5μm band,the integrated radiation intensity initially rises and then declines with the increase of detection angle,peaking at α=5°;in the 8-14μm band,the integrated radiation intensity follows a similar trend but peaks at α=90°.When the aircraft surface emissivity decreases from 0.9 to 0.1,on the horizontal detection plane, at α =45°, the integrated radiation intensity of the 8～14μm band decreases by 78.6%; however, the integrated radiation intensity of the 3-5μm band does not decrease,but increases by 2.56%.更多还原