The Research Of The Aerodynamics Of Vortex-controlled Aircraft

With the development of science and technology,future aircraft are required with the ability of high maneuverability and full-speed flight characteristics.Therefore,the aerodynamics design is mostly a large swept delta wing layout with a small aspect ratio.But this type of configuration is prone to produce asymmetric flow structures at high angles of attack,which may result in non-command deflection and serious flight accidents.In this paper,the experimental methods were used to study and utilize this asymmetric flow,mainly from the two aspects of the generation and development of this asymmetric flow and how to control this asymmetric flow.First of all,flow over high-sweep delta wing was measured with Particle Image Velocimetry to analyze the origination and development of asymmetric flow,then the pressure distribution,the force characteristic tests were conducted to get the influence of the asymmetric flow over delta wing.To effectively utilize this asymmetric flow,an aircraft model was designed,which uses the aircraft precursor to amplify the asymmetric disturbance of the aircraft apex and finally generate a strong asymmetric flow on the main wing of the aircraft.The flow and force pattern of the fore-body of aircraft model were obtained to throw light on the asymmetric flow of the model fore-body.Last,the mechanical properties of the aircraft and the surface pressure characteristics were got.The results show that the reason for the rolling moment of this type of large swept delta wing is the asymmetric flow over the model,and the flow characteristics of such models are very sensitive to the perturbation of the model tip.The disturbance achieves control of the flow characteristics of the model and its aerodynamic characteristics.The designed aircraft precursor has a strong amplification effect on the asymmetric disturbance of the head,which can amplify the asymmetric disturbance and form a strong asymmetric flow on the main airfoil of the model,thus achieving aerodynamic control through small disturbance.