Generic lambda wing configuration with classical and novel control surfaces and highly integrated intakes

Abstract

A study on the aerodynamics of a generic tailless lambda wing configuration at transonic Mach numbers is reported with an emphasis on both, stability and control and the effect of an intake on the lee side of the vehicle. The SACCON (Stability And Control CONfiguration) represents a generic unmanned combat air vehicle configuration that has also been the subject of a task group of NATO’s Science and Technology Organization (STO). The effect of classical and novel control concepts has been tested in the transonic wind tunnel of the German–Dutch Wind Tunnels to determine their effects on the lateral directional and longitudinal stability of the aircraft. In addition, the influence of a highly integrated flow-through intake on the vortical flow about the generic configuration has been examined by considering two versions of the model: a clean one without intake, and a modified one with intake and exhaust openings on the lee side. Forces and moments were measured by a strain gauge balance, and the pressure distribution on the lee side of the model was determined by pressure-sensitive paint. The study has been complemented by an investigation of the combined effects of boundary layer ingestion and an S-duct diffuser on flow conditions at the engine face. The main focus of the investigations is on the impact of boundary layers on intake performance and on limitations of diverterless intakes due to boundary layer ingestion. To this end, the dependence on flow parameters of total pressure distortions in a generic intake has been examined in a parametric study in a blowdown wind tunnel. In order to form a boundary layer of well-defined thickness ahead of the intake the model was arranged on a flat plate.