Abstract The use of active, internally blown high-lift flaps causes the reduction of the stall angle of attack, because of the strong suction peak generated at the leading-edge. This problem is usually addressed by employing movable leading-edge devices, which improve the pressure distribution, increase the stall angle of attack, and also enhance the maximum lift coefficient. Classical leading-edge devices are the hinged droop nose or the more effective slat with a gap. The flow distortions generated by the gap become an important source of noise during approach and landing phases. Based on these considerations, the present work aims at evaluating the potentials of gap-less droop nose devices designed for improving the aerodynamics of airfoils with active high lift. Both conventional leading-edge flaps and flexible droop noses are investigated. Flexible droop nose configurations are obtained by smoothly morphing the baseline leading-edge shape. Increasing the stall angle of attack and reducing the power required by the active high-lift system are the main objectives. The sensitivities of the investigated geometries are described, as well as the physical phenomena that rule the aerodynamic performance. The most promising droop nose configurations are compared with a conventional slat device as well as with the clean leading-edge. The response of the different configurations to different blowing rates and angles of attack are compared and the stalling mechanisms are analyzed.
Assessment of leading-edge devices for stall delay on an airfoil with active circulation control
CEAS Aeronautical Journal ; 5 , 4
2014
Aufsatz (Zeitschrift)
Englisch
Assessment of leading-edge devices for stall delay on an airfoil with active circulation control
Springer Verlag | 2014
|Assessment of leading-edge devices for stall delay on an airfoil with active circulation control
Online Contents | 2014
|Control of Leading-Edge Airfoil Stall Using Pulsed Jets
AIAA | 2016
|Compressible Dynamic Stall Control Using a Variable Droop Leading Edge Airfoil
Online Contents | 2004
|