NUMERICAL SIMULATION OF AEROTHERMODYNAMIC CHARACTERISTICS OF FLOW OVER SPACE VEHICLE MODEL

摘要

In this work numerical simulation of flow overMartian space probe at wind tunnel conditions,corresponding to Mach numbers M = 7.5, 10. 5and 14 for various angles of attack is carriedout on basis of Navier-Stokes equations, whichare solved using in-house software packageHSFlow with possibility of distributedcomputing on multiprocessor computer.Peculiarities in behavior of aerodynamic andthermal characteristics of flow are discussed.