NUMERICAL SIMULATION OF AEROTHERMODYNAMIC CHARACTERISTICS OF FLOW OVER SPACE VEHICLE MODEL

摘要

In this work numerical simulation of flow over Martian space probe at wind tunnel conditions, corresponding to Mach numbers M = 7.5, 10. 5 and 14 for various angles of attack is carried out on basis of Navier-Stokes equations, which are solved using in-house software package HSFlow with possibility of distributed computing on multiprocessor computer. Peculiarities in behavior of aerodynamic and thermal characteristics of flow are discussed.