چكيده لاتين :
The three-dimensional supersonic turbulent flows over wrap-around fin missiles have been
computed using the Thin Layer Navier-Stokes (TLNS) equations to reduce the computational
efforts compared to those of the Full Navier-Stokes (FNS) equations. In this research, the
missile configuration is divided into multi regions to enable fluid flow simulation using Personal
Computers (PC). It also makes it possible to use a different number of nodes and distribution
of grids in each region to enhance the accuracy. The Thin Layer Navier-Stokes equations
in the generalized coordinate system were solved using an efficient, implicit, finite-difference
factored algorithm of the Beam and Warming. For the turbulent flow field computations, the
well-known isotropic two-layer algebraic eddy viscosity Baldwin-Lomax model was used. The
computations were performed for supersonic turbulent flows over wrap-around fin configurations
for free stream Mach numbers, Jlx =: 1.9 - 2.86. Predicted roll moment and longitudinal
aerodynamic coefficients were compared with the experimental data at various angles of attack.
The computational results are in good agreement with experimental data.
