Optimizing Supersonic Rocket Efficiency: a Numerical Analysis of Aerodynamic Characteristics and Angle of Canard Deflection

This paper deals with the numerical study of rocket aerodynamic characteristics. This rocket consists of a cylindrical body with a tapered nose, four flat plates at the front of the body, and four flat-plate rear fins arranged uniformly on the body. The calculation of the aerodynamic characteristics of an air-to-air rocket is done by varying the angle of attack as a function of Mach number by using the gambit mesh and the FLUENT solver. These forces are calculated by changing the angle of canard deflection. The Navier-Stokes equations for a 3D incompressible supersonic turbulent flow have been solved numerically by using the finite volume method. The results indicate the aerodynamic forces on the rocket peak at a specific deflection angle of the flat-plate. This indicates that improving the flat-plate deflection angle can lead to a more efficient and effective flow of the supersonic rocket.