Optimization of the rocket’s nose and nozzle design parameters in respect to its aerodynamic characteristics

The airflow around rockets with various nose cone and nozzle cone geometric parameters is investigated in this paper. The mathematical background and the computational model of airflow around the rocket are designed for that purpose. ANSYS CFX computer modeling software is used to compute the airflow velocities, pressure, airflow turbulence kinetic energy, drag force and drag coefficient dependencies on rocket flight velocity. Optimization of the rocket’s nose cone and nozzle cone geometry in respect to qualitative and quantitative parameters of rocket’s aerodynamic characteristics is performed.