B. Horvat, I. Yavrucuk

In this study, a mid-fidelity tightly coupled CFD/CSD framework using a Lattice-Boltzmann method fluid solver is validated against experimental rotor measurements conducted during hover and wind tunnel conditions. The study also includes UH60A rotor measurements in both wind tunnel and flight conditions. The rotor is simulated using two diferrent actuator disk approaches and an actuator line model. Furthermore, an internal Peters-He inflow model is used as a reference for validation. All inflow models are evaluated for their ability to predict rotor power, load distribution, blade motion and control input. The results indicate that all models have deficiencies in power prediction for the experimental rotor. Hover and wind tunnel blade load variations show good agreement. Results for the UH60A rotor are consistent with power estimates, blade flap, and control input. The framework is capable of simulating rotors, but the accuracy of power prediction depends on rotor geometry and is strongly affected by the treatment of blade tips in load computation.

49th European Rotorcraft Forum 2023, Bückeburg, 2023

Conference Paper

englisch

21,0 x 29,7 cm, 20 Seiten

DGLR-Bericht, 2023, 2023-01, 49th European Rotorcraft Forum 2023 - Proceedings; S.1-20; 2023; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

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2023