Numerical Aerodynamic Investigations on Missile Yawing Control Using Nose-Mounted Flow Effectors

摘要

Computational studies were performed for supersonic flow at a Mach number M = 1.5 past a generic slender body equipped with miniature flow effectors on its nose cone. Various flow-effector configurations were studied and compared with wind-tunnel data. The numerical results predicted the details of how the vortex systems were changed by the presence of the flow effectors, thereby affecting the side force magnitude. In general, the computationally determined force coefficients were in reasonable agreement with the experimental data. Both the numerical and wind-tunnel results showed that the peak side forces occurred at an angle of attack of approximately 17 deg, and the maximum side force occurred when the flow effector was situated in a forward position and on the side of the body at an angular position located 45 deg from the top of the missile. The numerical studies also showed that the side forces induced by the flow effectors could be as high as 25% of the normal forces on average. This supports the idea of using small devices on the nose of slender bodies to control the side forces.