The Impact and Mechanism Analysis of Effect of Incoming Flow Velocity on Aerodynamic of Flying Wing Model with Low Aspect Ratio

Abstract

With the development of modern air combat and the intensification of military confrontation, modern battlefields have put forward higher demands for the lift and drag characteristics and stealth characteristics of fighters. Because the configuration of flying wing with low aspect ratio removes the tail wing and adopts the wing body fusion design, its lift and drag characteristics and stealth are significantly better than the traditional configuration of wing body separation body. The configuration of flying wing with low aspect ratio has been widely concerned by aviation scientists from various countries and has been determined as the development direction of the future fighter configuration. Aircraft often fly at different speeds on the battlefield. Therefore, it is important to investigate the influence of different incoming flow speeds on the aerodynamic force of flying wing with low aspect ratio and to conduct mechanism analysis. In order to explore the influence of different incoming velocity on the aerodynamic coefficients of the configuration of flying wing with low aspect ratio and the underlying mechanism, the FL-24 wind tunnel of the China Aerodynamics Research and Development Center High Speed Institute conducted a test of the standard model of the flying wing with low aspect ratio. The test with flow Mach number of 0.4, 0.6, 0.8 obtained the normal force coefficient curve and found that the normal force coefficient decreases with the increase of Mach number at high angles of attack. The IDDES turbulence model is used to numerically calculate the standard mode, and the specific flow field details are obtained to explain the flow mechanism behind the phenomenon.