Nonequilibrium hypersonic flow of gas past a wing of small aspect ratio (Q2266644)

In the present paper, the thin shock layer method [the authors, Dokl. Akad. Nauk SSSR 234, 1032-1034 (1977; Zbl 0379.76057)] is used to consider the problem of nonequilibrium hypersonic flow of gas past a wing of small aspect ratio at an angle of attack. It is shown that the flow component of the vorticity is conserved along the streamlines, and this property is exploited to obtain an analytic solution of the equations of the three-dimensional nonequilibrium shock layer. The influence of the disequilibrium on the thickness of the shock layer and the pressure distribution is investigated.