Rotating Projectile / Missile Magnus Effect Numerical Calculation

In order to simplify the control system, many anti-tank and air launched missiles get stability by spinning about its axis with high angular velocity. The combination of missile's spinning and incidence of the flight will create Magnus force and moment. This phenomena is called Magnus effects.Magnus effect on slender bodies is due to the spinning and cross flow. The aberrance of boundary layer and centrifugal force result in asymmetry of pressure distribution between the two sides of slender body, and an extra side force-Magnus force-appears. Magnus effect on tail attributes to interaction between body and tail, oblique fixed or oblique cut tail and blunt trailing edge of thin tail fin. Although the magnitude of Magnus force is small, typically 1/10 to 1/100 of the normal force, the Magnus moment can be of sufficient magnitude to affect shooting precision even damage the dynamic stability as well. Detailed research about Magnus effects will help to guide the design of aerodynamic configurations and control systems.In this thesis, Navier-Stokes equations are solved with cell centered finite volume scheme to simulate the flow fields around spinning projectiles and missiles. The convective terms are discretized using upwind flux-difference-splitting technique of Roe. An implicit approximate factorization method is used to advance in time. The flow field around spinning projectile is acquired through steady computation. For the simulation of spinning missile, dual-time method and dynamic mesh technique are employed in the unsteady simulations. During the iteration process, the angular velocity of the missiles depend on rolling moment and the angular velocity in the past time step. The time converged angular velocity is decided with the work done by the rolling moment in one period is equal to zero. The aerodynamic characteristics is the periodic average value of the rotating missile. The computational results of the projectile have a good agreement with the experimental results. And the computational results of spinning missiles give reasonable prediction of the aerodynamic characteristics of missiles with oblique fixed or oblique cut tail.