Shock Control Bump and Cruise Flap for a NLF Aerofoil

Kurzfassung

Within the Smart Fixed Wing Aircraft – ITD of the Clean Sky Project a new transonic laminar aerofoil was investigated numerically respective to a possible drag reduction. These aerofoils show a strong drag rise for Off-Design Mach numbers due to increased wave drag. One possible method to reduce wave drag is the use of a shock control bump. Variations of bump position, bump height and crest positon are presented. Succesful reductions of wave drag are presented under Off-Design conditions. For those regions affected adversely by the bump a cruise flap is applied to control shock position and thus the effectiveness of the shock control bump.