Research on the influence of integrated infrared suppressor exhaust angle on exhaust plume and helicopter infrared radiation

Abstract

A numerical investigation is performed in the current study to illustrate the influences of exhaust angle of the integrated infrared suppressor on plume flow and helicopter infrared radiation, under the hover and cruise statuses. Three exhaust models are concerned, including the exhaust direction at 60°, 45°, and 18° angles to the horizontal plane. The results show that the heating effect of the exhaust plume on the fuselage is modified with the decrease of the exhaust angle. However, the decrease in exhaust angle will reduce the pumping coefficient of the mixing duct to some extent, resulting in an increase of exhaust temperature. For the model with an exhaust angle of 18°, three sets of comparative tests were designed. The results show that when there is no airflow outlet at the bottom of the fuselage, the surface temperature of the fuselage will increase significantly, and the position of the airflow outlet at the bottom of the fuselage also has a certain influence on the temperature field of the fuselage. On the horizontal detection plane, the infrared radiation intensity of the model with an exhaust angle of 60° and 45° is significantly lower than that with an exhaust angle of 18°. In the vertical detection plane, especially in the direction below the fuselage, the infrared radiation intensity of the model with an exhaust angle of 18° is the smallest. When compared to the hover status, the cruise status reduces the infrared radiation intensity somewhat.