Aspects of Shock Control and Adaptive Wing Technology

Abstract

The development of the boundary layer and shock boundary layer interaction es-sentially determine the performance boundaries of transonic transport aircraft. Employing shock and boundary layer control has therefore a large potential for improving flight perform-ance in terms of cruise drag and with regard to the drag-rise and buffet boundaries. Various means of shock and boundary layer control are described and aerodynamic performance im-provements due to control discussed. Shock conditions and critical stages in the development of the boundary layer on a wing are, however, strongly dependent on freestream conditions which change considerably during a typical aircraft flight mission. In order to optimize per-formance at all points of the flight envelope, the effective wing geometry and other means of control must therefore adjust to these changing conditions. Adaptive wing aspects are, conse-quently, being addressed.