Boundary Layer Separation in 2 and 3 Dimensional High Speed Blow

摘要

Laminar boundary flow on cones in supersonic flow was calculated using a modified Method of Integrals to account for the change in velocity profiles in the separated regions. The work was extended to three dimensions and compared to experimental data. Significant progress was made in the modeling of th flows and in particular the regions of separated and reverse flow in the boundary layer.