Part I The Flow Pattern on a Tapered Sweptback Wing at Mach Numbers between 0. 6 and 1.6nPart II Experiments with a Tapered Sweptback Wing ofnWarren 12 Planform at Mach Numbers between 0.6 and 1.6

摘要

The development of the flow pattern on a swept wing with incidence and stream Mach number is described.nIt is shown that the flow pattern at moderate incidences develops smoothly from a subsonic type involving leading-edge separation to a supersonic type where the flow is attached near the leading edge and with shock-induced separation further aft. The formation and movement of the shock-wave system and the vortices near the wing surface are briefly discussed.