Detailed mean-flow and turbulence measurements have been made in the boundary layer in the plane of symmetry of a body of revolution at incidence. These data and the somewhat limited information available from previous experiments are utilized, together with extensive plane-of-symmetry boundary-layer calculations in laminar and turbulent flows, to determine the most important effects of mean-flow convergence and divergence. (Author).

Three-dimensional compressible boundary-layer equations are particularized to the windward symmetry plane of a spherically blunted axisymmetric body at incidence under hypersonic conditions. Through the use eddy transport and streamwise intermittency both transitional and fully turbulent boundary layers may be treated. A scheme is presented for determining the outer-edge boundary conditions based on a mass flow balance treatment of the boundary-layer entrainment of the inviscid flow. A finite-difference technique is described for solving the set of partial differential equation governing the boundary-layer flow, and for treating the streamline-swallowing phenomenon.

Formulation and application of a windward plane of symmetry laminar, transitional, and turbulent boundary-layer analysis is presented for sharp cones at incidence in a supersonic or hypersonic flow. The governing boundary-layer equations in the plane of symmetry are numerically integrated on a digital computer using a marching implicit finite-difference technique. A so-called invariant model of turbulence is used in a two-layer eddy viscosity-mixing length approach for calculation of the turbulent boundary layer in conjunction with an intermittency factor treatment of the transition zone. Comparison of the of the present theory with experimental data is made.

Both laminar and turbulent flows in strongly curved ducts, channels, and pipes are studied by numerical methods. The study concentrates on the curved square-duct geometry and flow conditions for which detailed measurements have been obtained recently by Taylor, Whitelaw, and Yianneskis. The solution methodology encompasses solution of the compressible ensemble-averaged Navier-Stokes equations at low Mach number using a split linearized block implicit (LBI) scheme, and rapid convergence on the order of 80 noniterative time steps is obtained. The treatment of turbulent flows includes resolution of the viscous sublayer region. A series of solutions for both laminar and turbulent flow and for both two- and three-dimensional geometries of the same curvature are presented. The accuracy of these solutions is explored by mesh refinement and by comparison with experiment. In summary, good qualitative and reasonable quantitative agreement between solution and experiment is obtained. Collectively, this sequence of results serves to clarify the physical structure of these flows and hence how grid selection procedures might be adjusted to improve the numerical accuracy and experimental agreement. For a three-dimensional flow of considerable complexity, the relatively good agreement with experiment obtained for the turbulent flow case despite a coarse grid must be regarded as encouraging. (Author).