Application of Shock and Boundary Layer Control to a Business-jet Aircraft

Summary

The present paper describes the application of shock and boundary layer control to a business-jet aircraft similar to the Dassault Falcon. It is comprised of the aerodynamic assessment of the effect of a bump on the flow development about a Falcon-type airfoil at design and off-design conditions, the technological integration of control by an adaptive bump and slot suction, respectively, into a Falcon-type wing, and the assessment of minimum benefits making an introduction of control worthwhile. It was found that for the turbulent Falcon wing an adaptive bump is required. Installation penalties for such a bump are assessed to be around 3% of total drag, so the bump does not show sufficient performance to be introduced into the present turbulent wing and, as a consequence, a new wing design is needed whose aerodynamic behavior in the transonic regime must include a very constant shock position. For slot suction, an estimation of the suction power accessible on the FALCON allows the operation of a suction system at rates compatible to the ones studied in Task 3, however, the costs of implementation correspond to more than 6% in total drag with gains being limited to 2% so that such a system is not a viable tool for drag reduction for the present aircraft.