Aerodynamics of Gust Load Alleviation on a Forward Swept Aircraft Configuartion
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Beschreibung
This thesis presents a novel approach to alleviate gust loads through spanwise lift and moment control. The method applies distributed actuators located along the leading and trailing edge of the wing. The focus is put on a forward swept configuration being derived from the backward swept DLR LEISA configuration and can handle both subsonic and transonic flow conditions. The trailing edge actuators are capable of regulating gust-induced lift, ensuring that the elliptical lift distribution is maintained during gust encounters. However, the forward swept configuration is characterised by a relatively high trailing edge sweep, which reduces the load reduction potential of the actuators. As a result, increased deflection angles are necessary to maintain cruise conditions during gust encounters compared to the backward swept configuration. Moreover, it can be noticed that the deflection of the trailing edge actuators generates an additional pitching moment, which can be controlled through the use of leading edge actuators.
Autor*in
Lorenz Klug
Themen in »Aerodynamics of Gust Load Alleviation on a Forward Swept Aircraft Configuartion«
Active Gust Load Alleviation Forward Swept Wing Aircraft Aerodynamics Aircraft Design Transonic Fluid Mechanics Computational Aerodynamics