Sliding mesh algorithm for CFD analysis of helicopter rotor–fuselage aerodynamics

International Journal for Numerical Methods in Fluids - Tập 58 Số 5 - Trang 527-549 - 2008
R. Steijl1, George N. Barakos1
1Laboratory of Computational Fluid Dynamics, Department of Engineering, University of Liverpool, Liverpool L69 3GH, U.K.

Tóm tắt

AbstractThe study of rotor–fuselage interactional aerodynamics is central to the design and performance analysis of helicopters. However, regardless of its significance, rotor–fuselage aerodynamics has so far been addressed by very few authors. This is mainly due to the difficulties associated with both experimental and computational techniques when such complex configurations, rich in flow physics, are considered. In view of the above, the objective of this study is to develop computational tools suitable for rotor–fuselage engineering analysis based on computational fluid dynamics (CFD).To account for the relative motion between the fuselage and the rotor blades, the concept of sliding meshes is introduced. A sliding surface forms a boundary between a CFD mesh around the fuselage and a rotor‐fixed CFD mesh which rotates to account for the movement of the rotor. The sliding surface allows communication between meshes. Meshes adjacent to the sliding surface do not necessarily have matching nodes or even the same number of cell faces. This poses a problem of interpolation, which should not introduce numerical artefacts in the solution and should have minimal effects on the overall solution quality. As an additional objective, the employed sliding mesh algorithms should have small CPU overhead. The sliding mesh methods developed for this work are demonstrated for both simple and complex cases with emphasis placed on the presentation of the inner workings of the developed algorithms. Copyright © 2008 John Wiley & Sons, Ltd.

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Tài liệu tham khảo

FreemanCE MineckRE.Fuselage surface pressure measurements of a helicopter wind‐tunnel model with a 3.15‐meter diameter single rotor. NASA TM‐80051 1979.

ChaffinMS BerryJD.Navier–Stokes and potential theory solutions for a helicopter fuselage and comparison with experiment. NASA TM‐4566 June1994.

10.1016/0021-9991(86)90141-5

10.1016/0021-9991(86)90056-2

Barakos G, 2001, A fully distributed unstructured Navier–Stokes solver for large‐scale aeroelasticity computations, The Aeronautical Journal, 105, 419, 10.1017/S0001924000012392

10.1016/0021-9991(83)90106-7

10.1016/0021-9991(81)90210-2

EliassonP WandD MeijerS NordströmJ.Unsteady Euler computations through non‐matching and sliding‐zone interfaces. Thirty‐sixth Aerospace Sciences Meeting and Exhibit Reno U.S.A. 12–15 January 1998; AIAA Paper 1998‐0371.

PahlkeK Van der WallB.Calculation of multibladed rotors in high‐speed forward flight with weak fluid–structure‐coupling. Twenty‐seventh European Rotorcraft Forum Moscow Russia September 2001.

RenaudT BenoitC BonifaceJ‐C GardareinP.Navier–Stokes computations of a complete helicopter configuration accounting for main and tail rotor effects. Twenty‐ninth European Rotorcraft Forum Friedrichshafen Germany September 2003.

10.2514/1.11484

PotsdamM YeoW JohnsonW.Rotor airloads prediction using loose aerodynamic/structural coupling. American Helicopter Society 60th Annual Forum Baltimore MD 7–10 June 2004.

ParkY NamHJ KwonOJ.Simulation of unsteady rotor–fuselage aerodynamic interaction using unstructured adaptive meshes. Fifty‐ninth Annual Forum of the American Helicopter Society Phoenix AZ 6–8 May 2003.

Park Y, 2004, Simulation of unsteady rotor flow field using unstructured adaptive sliding meshes, Journal of the American Helicopter Society, 49, 391, 10.4050/JAHS.49.391

10.4050/JAHS.51.141

BarakosG SteijlR BadcockK BrocklehurstA.Development of CFD capability for full helicopter engineering analysis. Thirty‐first European Rotorcraft Forum Florence Italy 13–15 September 2005.

10.1002/fld.1086

SteijlR BarakosG.CFD analysis of rotor–fuselage interactional aerodynamics. Forty‐fifth AIAA Aerospace Sciences Meeting and Exhibit Reno Nevada U.S.A. 8–11 January 2007; AIAA Paper 2007‐1278.

10.1016/S0376-0421(00)00005-1

JamesonA.Time dependent calculations using multigrid with applications to unsteady flows past airfoils and wings. AIAA Paper 91‐1596 1991.

10.2514/1.5177

10.2514/1.8830

Van Albada GD, 1982, A comparative study of computational methods in cosmic gas dynamics, Astronomy and Astrophysics, 108, 76

MineckRE Althoff GortonS.Steady and periodic pressure measurements on a generic helicopter fuselage model in the presence of a rotor. NASA TM 210286 2000.

ElliotJW AlthoffSL SaileyRH.Inflow measurements made with a laser velocimeter on a helicopter model in forward flight Volume 1 Rectangular planform blades at an advance ratio of 0.15. NASA TM 100541 1988.

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Thông tin xuất bản

International Journal for Numerical Methods in Fluids

Tập 58 Số 5

527-549

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