Hypersonic flow over bodies in tandem

Abstract.

A computational study of hypersonic flow over two bodies in tandem was made with the aim to understand the problems that may be encountered when the drag of a ballute is used to decelerate a spacecraft in the outer atmosphere of a planet for aerocapture. When the trailing body is large, shock-shock interaction causes the flow to become violently unsteady. This can be avoided by making the second body in the shape of a ring. Several configurations are examined, and the interesting phenomena that occur are discussed.