Application of an Adaptive Shock Control Bump for Drag Reduction on a Variable Camber NLF Wing

Abstract

A numerical study concerning the application of a finite pan shock control bump (SCB) on a natural laminar flow (NLF) wing was performed. To assess the potential Performance gain by using a combination of a deployable SCB and variable camber (VC), several parametric studies have been carried out. They were performed on a threedimensional halfmodel of an NLF wing. Results will be presented concerning the effect of shock Position and SCB height on the achievable drag reduction. Additionally, results concerning the effect of VC on drag as well as its application as a means to correctly position the shock with regard to the SCB will be presented. For the given geometry, a maximum drag re- duction of up to 5.6% was achieved. The work presented in this paper was done in the LDAinOP project (Low Drag Aircraft in Operation), as a part of the German national research project LuFoV-1, in cooperation with Airbus and the University of Stuttgart.