Lambda wing configurations are known to possess challenging flight characteristics at transonic Mach numbers. This study tests various methods for increasing the maneuverability and stability of the SACCON, a generic lambda wing configuration. Several control concepts are presented and tested to determine their effects on the lateral-directional and longitudinal stability of the aircraft. The first category of control concepts uses smooth surface deformations of the wing tips to eliminate control surface gaps found with traditional flap-based systems. The second category uses panel deflections on the upper surface of the aircraft. Each concept is simulated at Mach numbers in the range of 0.5≤M∞≤0.85 using the TAU code of the German Aerospace Center (DLR), with subsequent wind tunnel tests taking place in the Transonic Wind Tunnel of the German–Dutch Wind Tunnels (DNW-TWG) in Göttingen, Germany. The main flow features created by each control device and the Mach number effects are discussed, as are their effects on the aircraft’s aerodynamic performance. The smooth wing-tip deformations isolate the control derivatives and are best able to enhance lateral-directional stability. The upper surface devices create a more complicated response but offer more immediate application due to their reliance on firmly established technology.
Transonic Numerical and Experimental Evaluation of Unconventional Lambda Wing Control Surfaces
Journal of aircraft ; 54 , 3 ; 1139-1149
2017
Article (Journal)
English
Transonic Numerical and Experimental Evaluation of Unconventional Lambda Wing Control Surfaces
Online Contents | 2016
|British Library Conference Proceedings | 2016
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