ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Research on the Influence of Flight Parameters on Helicopter Rotor BVI Noise Characteristics
Received date: 2012-12-17
Revised date: 2013-04-26
Online published: 2013-05-17
Supported by
Priority Academic Program Development of Jiangsu Higher Education Institutions(PAPD);Fundamental Research Funds for the Central Universities(NS2012035)
Rotor blade-vortex interaction (BVI) is a complex aerodynamic phenomenon of the helicopter. In this paper, a coupled Eulerian-Lagrangian method is established for impulsive air-loading prediction during interaction. The flow field is divided into two zones. A Navier-Stokes code is used to model the tip vortex formation around the blade, while a free wake model is employed in the vortex transport area to account for the effect of the far wake. The noise prediction is based on the well-known FW-H equation for acoustic pressure. With this method, a parametric study is performed to examine the effects of the descent angle, advance ratio and thrust coefficient on the BVI noise of an AH-1/OLS rotor. BVI noise has the typical feature of impulsivity and strong directivity. It may propagate in multiple directions down and forward of the helicopter because several interaction events occur on the rotor. The BVI noise can be reduced by increasing the miss-distance of parallel interactions with proper descent angle and forward speed adjustment. However, decrease or increase in thrust coefficient changes only the direction of propagation, but not its magnitude.
SHI Yongjie , XU Guohua . Research on the Influence of Flight Parameters on Helicopter Rotor BVI Noise Characteristics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(11) : 2520 -2528 . DOI: 10.7527/S1000-6893.2013.0226
[1] Yu Y H.Rotor blade-vortex interaction noise.Progress in Aerospace Sciences,2000,36(2): 97-115.
[2] Tung C,Yu Y H.Aerodynamic aspects of blade-vortex interaction (BVI).AIAA-1996-2010,1996.
[3] Yu Y H,Tung C,Gallman J,et al.Aerodynamics and acoustics of rotor blade-vortex interactions; analysis capability and its validation.AIAA-1993-4332,1993.
[4] Chung K.Numerical predictions of rotorcraft unsteady air-loadings and BVI noise by using a time-marching free-wake and acoustic analogy.31st European Rotorcraft Forum,2005.
[5] Strawn R C,Caradonna F X,Duque E P N.30 years rotorcraft computational fluid dynamics research and development.Journal of the American Helicopter Society,2006,51(1): 5-21.
[6] Kim J W,Park S H,Yu Y H.Euler and Navier-Stokes simulations of helicopter rotor blade in forward flight using an overlapped grid solver.AIAA-2009-4268,2009.
[7] Kang H J,Kwon O J.Unstructured mesh Navier-Stokes calculations of the flow field of a helicopter rotor in hover.Journal of the American Helicopter Society,2002,47(2): 90-99.
[8] Gennaretti M,Bernardini G.Novel boundary integral formulation for blade-vortex interaction aerodynamics of helicopter rotors.AIAA Journal,2007,45(6): 1169-1176.
[9] Hu H,Jordan L A,Bader J D.CFD investigation of double-swept blade in BVI noise reduction.AIAA-2003-3172,2003.
[10] McAlister K W,Tung C,Heineck J T.Forced diffusion of trailing vorticity from a hovering rotor.Proceedings of 57th Annual Forum of AHS,2001.
[11] van der Wall B G,Yin J P.Prediction of BVI noise radiation variation due to HHC using advanced prescribed wake methodology.Proceedings of 68th Annual Forum of AHS,2012.
[12] Fogarty D E,Wibur M L,Sekula M K,et al.Prediction of BVI noise for an active twist rotor using a loosely coupled CFD/CSD method and comparison to experimental data.Proceedings of 68th Annual Forum of AHS,2012.
[13] Schmitz F H,Sim B W.Radiation and directionality characteristics of helicopter blade-vortex interaction noise.Journal of the American Helicopter Society,2003,48(4): 253-269.
[14] Farassat F,Succi G P.The prediction of helicopter rotor discrete frequency noise.Vertica,1983,17(4): 309-320.
[15] Roe P L.Approximate Riemann solvers,parameter vectors,and difference schemes.Journal of Computational Physics,1981,43(2): 357-372.
[16] Luo H,Baum J D.A fast,matrix-free implicit method for computing low Mach number flows on unstructured grids.AIAA-1999-3315,1999.
[17] Xu G H,Newman S J.A full-span free-wake model using circular-arc vortex elements and incorporating rotor trim analysis.Proceeding of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering,2006,220(2): 145-153.
[18] Shi Y J,Zhao Q J,Xu G H.Numerical calculation and parametric study of aerodynamics of rotor blade-vortex interaction.Acta Aeronautica Astronautica Sinica,2010,31(6): 1106-1114.(in Chinese) 史勇杰,招启军,徐国华.旋翼桨-涡干扰气动特性计算及参数影响研究.航空学报,2010,31(6): 1106-1114.
[19] Boxwell D A,Schmitz F H,Splettstoesser W R,et al.Helicopter model rotor-blade vortex interaction impulsive noise: scalability and parametric variations.Journal of the American Helicopter Society,1987,32(1): 5-12.
[20] Shi Y J,Zhao Q J,Xu G H.An analytical study of parametric effects on rotor-vortex interaction noise.Proceedings of the Institution of Mechanical Engineers Part G-Journal of Aerospace Engineering,2011,225(3): 259- 268.
/
| 〈 |
|
〉 |
CJA