The small parameter method (SPM) proposed in [1, 2] for calculating a three-dimensional, laminar, viscous shock layer is developed further. This method is widely used for solving the problem of a three-dimensional supersonic flow of a viscous gas about bodies in view of the agitation of the flow to turbulence and the occurrence of equilibrium physicochemical processes. To describe a turbulent flow of ionized and dissociated air, a three-dimensional system of complete equations for a viscous shock layer (CVSL), written in semi-simplest form , is used. The viscosity coefficient and Prandtl number for turbulent flow are calculated with equations developed from the two-layer algebraic model proposed in . The system of equations arising as a result of application of the SPM is solved numerically by global iterations [1, 2]. Calculations are carried out for flow about long blunted bodies at small angles of attack in a wide range of Reynolds and Mach numbers. A comparison of numerical and experimental data shows that the proposed method allows one to determine with high accuracy both the local and the integral characteristics of the flow and may be effectively used to simultaneously solve ballistics and flow problems . The characteristic time for calculating one variation of the problem took 30-40 min in an IBM PC/AT-386/387.
|Number of pages||6|
|Publication status||Published - Jul 1996|