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CFD simulation of helicopter rotor flow based on unsteady actuator disk model 被引量:9
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作者 G.N.BARAKOS T.FITZGIBBON +2 位作者 A.N.KUSYUMOV S.A.KUSYUMOV S.A.MIKHAILOV 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2020年第9期2313-2328,共16页
Actuator Disks(AD)can provide characterizations of rotor wakes while reducing computational expense associated with modeling the fully resolved blades.This work presents an unsteady actuator disk method based on surfa... Actuator Disks(AD)can provide characterizations of rotor wakes while reducing computational expense associated with modeling the fully resolved blades.This work presents an unsteady actuator disk method based on surface circulation distribution combined with empirical data,blade element theory and rotor momentum theory.The nonuniform circulation distribution accounts for 3 D blade load effects,and in particular,tip loses.Numerical simulations were conducted for the isolated pressure sensitive paint model rotor blade in hover and forward flight using the HMB3 CFD solver of Glasgow University.Validation of CFD results in comparison with published numerical data was performed in hover,for a range of blade pitch angles using fully turbulent flow and the k-x SST model.In forward flight,the vortex structures predicted using the unsteady actuator disk model showed configurations similar to the ones obtained using fully resolved rotor blades.Despite the reduced grid cells number,the CFD results for AD models captured well the main vortical structures around the rotor disk in comparison to the fully resolved cases. 展开更多
关键词 CFD Fully resolved blades rotor PSP rotor Surface circulation distribution Unsteady actuator disk model
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