Research on Wind Tunnel Test of Aerodynamic Characteristics of Missile under Subtransonic Velocity

Abstract

In the process of missile design, the aerodynamic characteristics of missile as an important factor directly affect the dynamic quality of missile flight. In the case of severe nonlinearity of aerodynamic characteristics in subsonic and transonic regions, the aerodynamic calculation accuracy provided by engineering estimation and CFD numerical calculation method is limited, which leads to low identification accuracy of rudder efficiency characteristics, so it is necessary to calculate aerodynamic parameters accurately by wind tunnel test method to determine the rudder efficiency of missiles. The influence of Mach number of missile flight on aerodynamic characteristics of missile in subsonic and transonic speed is studied by means of wind tunnel test method, and the driving efficiency of rudder is analyzed according to aerodynamic characteristics. The results show that, with the increase of Mach number, the aerodynamic characteristics of the missile are basically the same as at subsonic speed; the pitch rudder efficiency of the missile is increased first and then decreased, while the roll rudder efficiency is decreased first and then increased at subtransonic speed.

Keywords

• missile wind tunnel test
• subtransonic
• aerodynamic performance
• rudder efficiency characteristic