Transonic Numerical and Experimental Investigation into Unconventional Lambda Wing Control Surfaces

Abstract

Lambda wing configurations are known or possess challenging flight charcteristics at transonic Mach numbers. The DLR-17E model is category as the numerical and experimental test vehicle for the present study. The first category of control concepts uses smooth surface deformations of the wingtips to eliminate traditional control surface gaps. The second category uses quick Panel deflections on the upper surface of the aircraft. Each concept was simulated at Mach numbers between 0.5 and 0.85 using the DLR TAU code, with subsequent wind tunnel tests taking place in the Transonic Wind Tunnel (DNW-TWG) in Göttingen. The numerical an experimental results are used to evaluate the CFD code's ability to aid in the Initial design process. The main flow features created by each control device and the Mach number effects are discussed, as well as their effects on the aircraft's aerodynamic performance.