Application of DDES method to simulation of complicated rotor flowfield

DONG Jun; YE Liang

doi:10.7527/S1000-6893.2018.21689

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2018 , Vol. 39 >Issue 6: 121689 - 121689

DOI: https://doi.org/10.7527/S1000-6893.2018.21689

Fluid Mechanics and Flight Mechanics

Application of DDES method to simulation of complicated rotor flowfield

DONG Jun ,
YE Liang

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AVIC Aerodynamics Research Institute, Shenyang 110034, China

Received date: 2017-08-23

Revised date: 2018-02-09

Online published: 2018-02-09

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Abstract

Characteristics of rotorcraft flow fields which contains complicated airflow detached phenomenon are simulated by Delayed Detached Eddy Simulation (DDES). The embedded grid system constructed by combining adaptive background Cartesian and body-fitted grid is adopted to simulate simultaneously the flow separation in the near wall region and the wake evolution in far fields when the computation resource is limited. The flow fields iteration, hole cutting and donor searching processes are parallelized based on the message passing library (distributed-memory parallelization) to improve computing efficiency. Flow fields of a coaxial rotor in hover and a single rotor in descending state are simulated, aiming to discuss the differences where large range of flow separations near the blade surface region exist or not with DDES and Reynolds-averaged Navier-Stokes method. Results show that in the descending status, more strengthen separations and unsteady phenomenon are predicted in the rotor wake with DDES, the predicted coaxial rotor flow fields are similar with different methods, as the attached flow is dominated with moderate collective blade angle, the slim discrepancy is observed only on the lower rotor blades aerodynamics and induced velocity beneath the rotor root.

Key words： rotor; flowfield; embedded grid; parallel computing; delayed detached eddy simulation (DDES)

Cite this article

DONG Jun , YE Liang . Application of DDES method to simulation of complicated rotor flowfield[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018 , 39(6) : 121689 -121689 . DOI: 10.7527/S1000-6893.2018.21689

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