3-DIMENSIONAL SUPERSONIC TURBULENT-FLOW ABOUT BODIES AT SMALL ANGLES OF ATTACK

The small parameter method (SPM) proposed in [1, 2] for calculating a three-dimensional, laminar, viscous shock layer is developed further T his method is widely used for solving the problem of a three-dimension al supersonic flow of a viscous gas about bodies in view of the agitat ion of the flow to turbulence and the occurrence of equilibrium physic ochemical processes. To describe a turbulent flow of ionized and disso ciated air, a three-dimensional system of complete equations for a vis cous shock layer (CVSL), written in semi-simplest form [3], is used. T he viscosity coefficient and Prandtl number for turbulent flow are cal culated with equations developed from the two-layer algebraic model pr oposed in [4]. The system of equations arising as a result of applicat ion of the SPM is solved numerically by global iterations [1, 2]. Calc ulations are carried out for flow about long blunted bodies at small a ngles of attack in a wide range of Reynolds and Mach numbers. A compar ison of numerical and experimental data shows that the proposed method allows one to determine with high accuracy both the local and the int egral characteristics of the flow and may be effectively used to simul taneously solve ballistics and flow problems [5], The characteristic t ime for calculating one variation of the problem took 30-40 min in an IBM PC/AT-386/387.