Aerodynamic Coefficients Investigation of GRAD Rocket using Computational Fluid Dynamics

Abstract

The article provides an aerodynamic characteristics investigation of GRAD Rocket using the computational fluid dynamic method. Computational analysis has been performed to predict the Aerodynamic characteristics of the GRAD rocket. A commercial software ANSYS FLUENT is used to simulate the unsteady aerodynamic characteristics of the missile while the Missile DATCOM software is used to confirm and validate the results. The simulations have been conducted out for a range of Mach number 0.4 to 3 versus angle of attack from 0° to 9°, through the sideslip angle 0° to 9°. The results represent that the Drag Coefficient is highly sensitive to the angle of attack and velocity region. The total drag of the missile is mainly generated from the missile's body, where they wrap around fins contribute only 18.45 percent of a total drag coefficient. In contrast, the lift coefficient increases with an increased angle of attack, but it decreases with changes of the region from subsonic to supersonic. The flow visualization of the static and dynamic pressure contours is illustrated. The Shock wave is captured at the nose and fins entrance. To verify the results, the simulations were carried out for two missile models. The first model represents the cylindrical body of the fin-less missiles, and the second one represents the rocket body with fins.