典型飞翼布局轰炸机气动与红外特性数值分析

Numerical Analysis of Aerodynamic and Infrared Radiation Characteristics of B2

以美国B2轰炸机作为研究对象,构建了进排气系统一体化整机仿真物理模型。计算了在不同飞行条件下轰炸机的气动/红外特性。结果表明:当飞行马赫数提高时,外流产生的对流换热加热蒙皮效果越发明显,跨声速飞行时,由于气动加热作用使机身前缘温度升高;水平方向上随着探测角度增加,3~5μm与8~14μm波段内轰炸机红外辐射强度降低;竖直方向探测时,3~5μm波段内轰炸机下方最大红外辐射强度值仅为上方最大值的20%,对规避来自地面及低空的红外探测具有重要意义;3~5μm波段内降低壁面发射率对轰炸机红外辐射的抑制效果在后方及上方探测角度内更为明显,最大降幅达60%;8~14μm波段内降低壁面发射率后轰炸机红外特征显著降低,最大降幅达70%。

In this paper,the B2 bomber is designed on the integrated inlet and exhaust system.The aerodynamic/infrared characteristics of the bomber under different flight conditions were calculated.The results show that when the flight Mach number is increased,the effect of convective heat transfer heating generated by the outflow is more and more obvious,and in the transonic flight,the temperature of the front edge of the fuselage increases due to the aerodynamic heating;In the horizontal direction,with the increase of detection Angle,the infrared radiation intensity of bomber decreases in the band of 3~5μm and 8~14μm band;In the vertical direction detection,the maximum infrared radiation intensity value below the bomber in the 3-5μm band is only 20%of the maximum value above,which is of great significance to avoid the infrared detection from the ground and low altitude;The suppression effect of reducing the wall emission rate in the 3~5μm band on the bomber infrared radiation is more obvious in the rear and upper detection Angle,with a maximum reduction of 60%;After reducing the wall firing rate in the 8~14μm band,the infrared characteristics of the bomber were significantly reduced,with a maximum reduction of 70%.