Numerical Simulation Of The Flow Around The
Helicopter Blade In Hover Using The
MRF Method And Turbulence Models
Author(s)
T. Azzam, T. Belmerabet, M. Mekadem, S. Djellal & S. Hanchi
Abstract
The aim of this study is to find the most adequate numerical model to simulate
the aerodynamics of the helicopter rotor in hovering flight, using CFD code
Fluent. In this work, the Caradonna and Tung blades are used with NACA0012
profile and an aspect ratio of six. The rotating rotor is modeled by the multiple
references rotating frame method (MRF). Using the periodicity condition,
computations are carried only on one blade. For grid generation, the structured
mesh is generated near the wall region with 30 y 300 and for the rest of the
computational domain, the unstructured mesh is used. The value of the near-wall
resolution yp depends on the value of the mean skin friction coefficient . f C
According to the study of Lombardi et al. (Numerical Evaluation of Airfol
Friction Drag. Journal of Aircraft, 2000), the value of f C can be considered
similar for both flat plat and NACA0012 airfoil. To evaluate the surface pressure
distributions, we have treated the effect of the collective pitch angle (θ), the tip
Mach number (Mtip) and the two turbulence models, standard k and Spalart-
Allmaras. The obtained results are expressed in terms of pressure coefficient Cp,
have been validated by comparisons with the experimental data. In addition, we
discuss in this study the prediction of shock location on the upper surface of the
blade.
Keywords: aerodynamic, helicopter blade, MRF, hovering flight, pressure
coefficient, shock wave.
Keywords
aerodynamic, helicopter blade, MRF, hovering flight, pressure
coefficient, shock wave
Related Book
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