Simulation study of aerodynamic parameters of small unmanned aerial vehicle (UAV) dropped munitions

Abstract Based on the method of computational fluid dynamics, fluent software is used to simulate and calculate the aerodynamic parameters of small unmanned aerial vehicle projectiles. The drag coefficient, lift coefficient, and pitching moment coefficient of the projectile under different angles of attack and different throwing velocities are obtained by establishing a three-dimensional model of the projectile, dividing the computational grid, and setting up the relevant initial conditions. The results are analyzed, and the results of the computation can provide a basis for the calculation of the ballistic trajectory of the projectile.