NUMERICAL-SIMULATION OF 3-DIMENSIONAL SUPERSONIC-FLOW AROUND AERODYNAMIC CONFIGURATIONS

The present report deals with many applications of different numerical methods to calculations of three-dimensional stationary supersonic flows around aerodynamic configurations. Both an inviscid non-heat-conducting perfect gas and a real high-temperature gas with physical-chemical processes are considered. The results of some investigations carried out during recent years in the U.S.S.R. are reviewed. A brief description of applicable numerical methods is presented. A number of results are discussed both for separate parts of a flying vehicle and for whole configurations. Some gasdynamic effects, and aerodynamic and thermal characteristics are analysed. Among the aerodynamic elements we consider pointed and blunted nose parts of configurations, air intakes, wing and stabilizers. Also more complicated cases are considered such as compound aerodynamic objects and configurations modelling different kinds of whole flying vehicles (missile, aircraft, spacecraft).