Calculation of flow around helicopter rotors in lifting forward flight requires a three-dimensional unsteady method. A boundary element method (Lifting Body Suface (LBS)) was successfully applied at DLR for the prediction of propeller aeroacoustics. Results from application to rotor aeroacustic for non-lifting hover showed good agreement with Euler solutions and with experiment. Boundary element methods based on linear potential theory are efficient and easy to handle even for complex geometries. The aim of this work is to check the applicability of the LBS method to the rotor in lifting foward flight for design purposes. The LBS method is a supplement to lifting line methods used at DLR for the aerodynamic computation of rotors. It offers higher flexibility in planforms and profiles of rotor blades and it provides pressure distributions on blade surfaces, important for acoustic calculations. The unsteady Euler methods also used at DLR are too expansive for design purpose at present time.
Prediction of rotor aeroacustic in forward flight by a lifting surface method
Die Prognose der Rotorblattakustik im Vorwärtsflug mittels einer Tragflächenmethode
1994
16 Seiten, 11 Bilder, 26 Quellen
Conference paper
English
Luftfahrttechnik , Hubschrauber , Flugmechanik , Rotor (Drehflügel) , akustische Emission , technische Entwicklung , Rechenmodell , Grenzschichtgleichung , Schweben , Vergleich (System) , Euler-Gleichung , experimentelle Untersuchung , Prozessoptimierung , Projektentwicklung , belastetes Bauteil , Druckverteilung , Profilumströmung
Prediction of Rotor Aeroacoustics in Forward Flight by a Lifting Surface Method
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