47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan
抄録（英）
The aerodynamic performance of a full-scaled helicopter rotor is predicted using a rotorcraft CFD solver, rFlow3D. The prediction accuracy is verified through comparison with the selected wind tunnel test data of a constant thrust while the advance ratio is increased up to 0.4. Trim adjustment is improved by implementing a look-up table for the sectional aerodynamics. The rotor control angles and rotor drag and power between prediction and experiment are found in acceptable agreement. Some differences in the collective and lateral pitch angles are observed due to not including the elastic deformations in the analysis. Detailed comparisons of the sectional airloads are also performed and good correlations are found. The aerodynamic loads in the reversed flow region are also obtained. The influence of the elastic deformation on the prediction accuracy of aerodynamic performance at high advance ratio conditions will be further studied.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
ヘリコプタの高速飛行時の空力性能予測
AA1630005018.pdf
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