Abstract. The hypersonic waverider forebody is designed in this paper. For the present waverider, the undersurface is carved out as a stream surface of a hypersonic inviscid flow field around wedge-elliptic cone, and the upper surface is assumed to be a freest ream surface. A finitevolume code is used to generate the three-dimensional flow field. The leading edge is determined by satisfying the condition that the lip is situated at the intersection line of shocks.
Compared to LEO reentry vehicles, the flow effect of the circumlunar free return and reentry flight vehicle is much more complex, and the aerodynamic data with high precision is required. The correctness and completeness of the aerodynamic design and verification is vital to the success of the lunar return mission. The aerodynamic characteristics of the mission is summarized, and the aerodynamic design method, calculations and experiments, data analysis method and its results for the reentry capsule, several specific aerodynamic problems and the research conclusious are also presented in this paper. The flight results show that the data achieved by areodynamic design and verification is well satisfied with the requirements of the mission. circumlunar free return, aerodynamic design method, calculations and experiments
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.