The present paper describes a new development of a computer code, the so called: Phoenix II, built up to predict the flowfield and the aerodynamic performance of helicopter rotors in hover. The original numerical resolution is based on a full potential method and allows to calculate the free convection of thin vorticals regions using a vortex embedding scheme. This modern helicopter aerodynamics approach has been recently improved and evaluated. The improvement has concerned the distribution of markers within the computational grid and the modelling of the vortical velocity in the entire domain of calculation including the immediate vicinity of the blade trailing edge. The modification of spatial weighting underrelaxation relative to the vortical component calculation has also been performed to stabilize the numerical scheme. Moreover, the axial velocities calculation has been modified by taking into account the axial velocity distribution provided at previous azimuths. The evaluation of this final code has been carried out from comparisons to experimental results obtained in the IRPHE/ASI facilities. Tests have concerned measurements of overall forces (thrust and torque), tip vortex paths, local velocities and radial distribution of circulation on model-scale of two and four bladed rotors in hover, at different pitch angles.
Flow field prediction for helicopter in hover using a vortex embedding method
Vorhersage des Strömungsfeldes für einen Hubschrauberrotor im Schwebeflug mit Hilfe einer Wirbeleinbettungsmethode
European Rotorcraft Forum, 23 ; 1 ; 3-10
1997
10 Seiten, 8 Bilder, 12 Quellen
Conference paper
English
Flow Field Prediction for Helicopter Rotor in Hover Using a Vortex Embedding Method
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