The increase of the incident flow relative velocity results in considerable changes of the rotor airflow behaviour. The paper discusses traditional assumptions and hypotheses of aerodynamic rotor models and their applicability for high relative velocity regimes. Based on the analysis the paper presents a mathematical model of rotor aerodynamics giving more complete description of its operation. The blade is simulated using a non-linear transient theory of a lifting surface with nonstationary stall zones. A system of skew sections is described to formulate blade spatial flow and to define rotor aerodynamic characteristics. The respective two-dimensional models are used to simulate blade section aerodynamics. The numerical results are also presented in the paper.
|Number of pages||8|
|Publication status||Published - 2005|
|Event||30th European Rotorcraft Forum - Marseilles, France|
Duration: 14 Sep 2004 → 16 Sep 2004
|Conference||30th European Rotorcraft Forum|
|Period||14/09/04 → 16/09/04|