The thin-layer compressible Navier-Stokes Equations are numerically solved, together with the Euler equations as a limited case, for the transonic flow past axisymmetric boattailed projectiles. Applied is a typical implicit approximate-factorization finite difference method, first developed by Beam and Warming and then extended to the general curvilinear coordinates by Steger. A Pulliam-type modification is also test-used. This modification transforms the coupled system of equations into an uncoupled diagonal form which requires less computational work. For steady state applications the resulting diagonal algorithm retains the same stability and accuracy as those characteristic to the original algorithm. Numerical solutions are presented for the inviscid as well as viscous turbulent transonic flows past axisymmetric projectile configuration, whose bottail angle is varied from 5 degrees to 15 degrees. The turbulence is expressed by a well-known algebraic model of Baldwin-Lomax type, applicable to the present axisymmetric flow with moderate separation. Details of the flow field solution such as surface pressure curves, and the field pressure contours, and the shear-layer velocity profiles are presented. Good qualitative comparison with the earlier experimental data was obtained and the critical boattail angle at which the boundary layer separates from the surface was also determined.
