Test experiments were performed and calculation methods were developed to study the structural loading of helicopter rotor blades and the resulting noise emission which can strongly reduce operational conditions of a helicopter. An optimized winglet was constructed which reduced rotor blade loading and rotor noise emission by changing position and structure of the wing tip vortices. The use of such winglets is especially advantageous in case of fast descent. In fast forward flight the flow at the winglet can become a problem due to the high angles of attack at the winglet; however, no separation phenomena at the winglet were observed.
Strukturbeanspruchung und Laermbelaestigung Bein Hubschrauber (Structural Loading and Noise Disturbance of Helicopters)
1988
25 pages
Report
Keine Angabe
Englisch