Numerical study on flow characteristics of high-pressure capturing wing configuration at subsonic, transonic and supersonic regime [高压捕获翼构型亚跨超流动特性数值研究]

作者：Wang H.; Li G.; Yang J.; Xiao Y.; Wang X.; Xu Y.; Xu X.; Cui K.

来源：Chinese Journal of Theoretical and Applied Mechanics, 2021, 53(11): 3056-3070.

DOI：10.6052/0459-1879-21-059

• Aerodynamic interference
• Computational fluid dynamics
• Flow separation
• High-pressure capturing wing
• Wide speed range

In order to study the flow characteristics of the high-pressure capturing wing (HCW) configuration at subsonic, transonic and supersonic regime, the conceptual configuration of the conical-cone airframe combined HCW was selected, and the typical state points were selected in the range of Mach number 0.3 to 3. The numerical simulation and analysis were carried out under zero angle of attack condition. The results show that in the speed range studied, since the vertical distance between the airframe and HCW at the symmetry plane was the smallest, the aerodynamic interference was the most obvious and gradually weakened along the span. As the Mach number increased, the flow field structure between the airframe and HCW was obviously different. The specific performance were as follows: when the Mach number was less than 0.5, no flow separation occurred, and when the Mach number was greater than 0.5, the obvious flow separation in the back section of the airframe began to appear. Since HCW and the airframe formed an equivalent channel that first contracted and then expanded, the pressure on the lower surface of HCW and the upper surface of fuselage both decreased first and then increased. After entering the transonic speed domain, under the influence of the HCW, the flow separation became more obvious. The shock wave began to appear between the airframe and HCW, and interacted with the separation zone, and a shock wave train appeared which resulted in significant pressure fluctuations on the lower surface of HCW. When the Mach number was 1.5, the shock wave position between the airframe and HCW reached the tail of the airframe, and separation zone almost disappeared. When Mach number continues to increase, the entire flow field presented a shock-dominated structure and the pressure distribution on the lower surface of HCW and the upper surface of fuselage gradually became flat.

• 单位
  中国科学院; 高温气体动力学国家重点实验室; 中国科学院大学