Investigation of Canard Missile with Planar and Grid Fins by using CFD Tool.

Abstract

The aerodynamic coefficients and flow surrounding a canard missile design were predicted using viscous computational fluid dynamics simulation. The computations were performed at speeds between 1.5 and 3.0. High-speed flight is possible with canard deflection angles of 0 to 10 degrees, as well as planar and grid tail fins. The estimated aerodynamic coefficients were found to be astonishingly close to those obtained in the wind tunnel once data from the wind tunnel was analysed. It is possible that the flow visualisations produced by this work could lead to a better understanding of flow physics and the development of superior canard and tail fin designs for missiles and rockets among other things. Planar fins have a negative roll impact because of the pressure difference between the lowered fin and the canard trailing vortices. Grid tail fins improved the canards' ability to roll at low supersonic speeds by increasing their rolling efficiency.