Abstract
Abstract With the development of various technologies, the demand for high Mach number (Mach number greater than 8) aircraft is increasing. The requirements for hypersonic drag reduction and thermal protection are constantly increasing. At the present stage, there are relatively few researches on hypersonic drag reduction and thermal protection schemes considering the real gas effect. It is necessary to further study the flow characteristics and rules, and the applicability of drag reduction and thermal protection schemes under high Mach numbers. In this paper, the cylindrical and spherical shapes with Mach 16.5 are simulated. A series of studies are carried out on the forward-facing cavity. It is concluded that the forward-facing cavity can provide a good thermal protection effect, but the drag reduction effect is not good. What is more, the space of the cavity is larger, the diameter is longer, the ratio of the depth and length of the cavity is smaller, and the thermal protection effect is better. In addition, the lip passivation of different configurations of shallow cavity and deep cavity was studied. It is found that different shapes have different results.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call