Computational Aerodynamic Analysis of Capsule Configurations Toward the Development of Reusable Rockets

摘要

Flowfields around Apollo-type conical configurations are numerically simulated by Reynolds-averaged Navier-Stokes computations at a wide range of angles of attack under subsonic through supersonic flows. Effects of the configuration parameters on the aerodynamic characteristics and their flow mechanisms were clarified based on the computed results. It turns out that the aerodynamic characteristics are mainly influenced by the separation position of the flow, the pressure level behind the body, and the wind-side high pressures. The shoulder radius has a great influence on the pressure level behind the body and the separation position, so that the aerodynamic characteristics, especially at base-first conditions, significantly change. The drag coefficient at base-first conditions becomes small for configuration with the large shoulder radius because of the increase of the lee-side pressure level. At both nose-first and base-first conditions, the fineness ratio has great influence on the location and the pressure level of the wind-side high pressures, which appear on the windward cone part, so that the lift, drag, and pitching-moment coefficients significantly change.