摘要：Based on finite volume method, the interaction between base jet and supersonic flow around the rocket is simulated by Navier-Stokes equations with SST k-ω turbulence model and implicit algorithm. The pressure contours, the streamline patterns, and the variation of the aerodynamic characteristics of the rocket with the flying altitude, Mach number, and the angle of attack are shown and analyzed. Numerical results demonstrate that in supersonic flow, the base jet has a noticeable effect on the surface pressure of the body and the tails, leading to the decreases of the coefficients of the normal force, the pitching moment, and the pressure center. Furthermore, the higher the flying altitude, the more grave decreases of the coefficients of the normal force, the pitching moment and the pressure center. However, with the increase of Mach number, the more grave the decreases of the normal force coefficient and the pitch moment coefficient are found, while the less grave decrease is found with the pressure center coefficient. With the increase of the angle of attack, the more grave decreases are found with the coefficients of the normal force and the pitching moment, while the decrease of the pressure center coefficient remains almost the same.
