Abstract
Based on FW-H equations and the CFD method, aeroacoustic characteristics of rotor during collective pitch aperiodic variation are calculated and analyzed. At first, a set of analysis method for aperiodic rotor aeroacoustic characteristics is developed. The aerodynamic and aeroacoustic characteristics of BO-105 rotor in hover and NACA rotor in a ramp increase of collective pitch are calculated, and the employed numerical analysis method is validated through comparisons with experimental data. Then, the aeroacoustic characteristics of the NACA rotor during an oscillating collective pitch is analyzed, and the sound pressure peak at different collective pitch is discussed in detail, and some conclusions are obtained.
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References
Bres GA, Brentner KS, Perez G, Jones HE (2004) Maneuvering rotorcraft noise prediction. J Sound Vib 275(5):719–738
Stephenson JH, Tinney CE, Greenwood E, Watts ME (2014) Time frequency analysis of sound from a maneuvering rotorcraft. J Sound Vib 333(21):5324–5339
Farassat F, Succi GP (1980) A review of propeller discrete frequency noise prediction technology with emphasis on two current methods for time domain calculations. J Sound Vib 71(3):399–419
Farassat F, Myers MK (1988) Extension of Kirchhoff’s formula to radiation from moving surfaces. J Sound Vib 123(3):451–460
Francescantonio PD (1997) A new boundary integral formulation for the prediction of sound radiation. J Sound Vib 202(4):491–509
Huang Z, Siozos-Rousoulis L, Troyer TD, Ghorbaniasl G (2018) Helicopter rotor noise prediction using a convected FW-H equation in the frequency domain. Appl Acoust 140:122–131
Chen S, Zhao Q, Ma Y (2019) An adaptive integration surface for predicting transonic rotor noise in hovering and forward flights. Chin J Aeronaut 32(9):2047–2058
Loiodice S, Drikakis D, Kokkalis A (2018) An efficient algorithm for the retarded time equation for noise from rotating sources. J Sound Vib 412:336–348
Chen H, Brentner KS, Lopes LV, Horn JF (2006) An initial analysis of transient noise in rotorcraft maneuvering flight. International Journal of Aeroacoustics 5(2):109–138
Saetti U, Villafana W, Wachspress D, Brentner KS, Horn JF (2016) Helicopter simulations with coupled flight dynamics, free wake and acoustics, AHS 72nd annual forum proceedings, West Palm Beach, FL, USA, May 2016
Greenwood E, Schmitz FH, Sickenberger RD (2015) A semiempirical noise modeling method for helicopter maneuvering flight operations. J Amer Helicopter Soc 60(2):1–13
Vouros S, Goulos I, Pachidis V (2019) Integrated methodology for the prediction of helicopter rotor noise at mission level. Aerosp Sci Technol 89:136–149
Gennaretti M, Bernardini G, Serafini J, Anobile A, Hartjes S (2017) Helicopter noise footprint prediction in unsteady maneuvers. Int J Aeroacoust 16(3):165–180
Renzoni P, D’Alascio A, Kroll N (2000) EROS-a common European Euler code for the analysis of the helicopter rotor flowfield. Prog Aerosp Sci 36(5–6):437–485
Spentzos A, Barakos G, Badcock K, Richards B (2006) Modelling three-dimensional dynamic stall of helicopter blades using computational fluid dynamics and neural networks. Proc Inst Mech Eng Part G: J Aerosp Eng 220(6):605–618
Zhao Q, Zhao G, Wang B, Wang Q, Shi Y, Xu G (2018) Robust Navier-Stokes method for predicting unsteady flowfield and aerodynamic characteristics of helicopter rotor. Chin J Aeronaut 31(2):214–224
Zhang K, Zhao Q, Zhang X, Xu G (2021) Analysis of rotor aerodynamic response during ramp collective pitch increase by CFD method. Proc Inst Mech Eng Part G: J Aerosp Eng 235(9):994–1007
Yoon S, Jameson A (1988) (1988) Lower–upper symmetric-Gauss–Seidel method for the Euler and Navier-Stokes equations. AIAA J 26(9):1025–1026
Jiao L, Liu X, Shi Z, Zhang W et al (2020) A two-dimensional temperature correction method for pressure-sensitive paint measurement on helicopter rotor blades. Exp Fluids 61(104):1–11
Zheng X, Wang X, Chen Z, Huang B (2019) Experimental study on aerodynamic noise of BO-105 rotor model, 2nd national conference on aerodynamic noise and control technology, Guiyang, China, August 8–10, 2019
Capenter PJ, Fridovich B (1953) Effect of a rapid blade pitch increase on the thrust and induced velocity response of a full-scale helicopter rotor. NACA TN 3044
Ananthan S, Leishman JG (2004) Transient helicopter rotor wakes in response to time-dependent blade pitch inputs. J Aircr 41(5):1025–1041
Acknowledgements
This study was co-supported by the National Natural Science Foundation of China (Nos. 12032012).
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Chen, X., Zhang, K., Zhao, Q., Wang, W., Chen, S. (2023). Analysis of Rotor Noise During Ramp Collective Pitch Increase by CFD Method. In: Lee, S., Han, C., Choi, JY., Kim, S., Kim, J.H. (eds) The Proceedings of the 2021 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2021), Volume 1. APISAT 2021. Lecture Notes in Electrical Engineering, vol 912. Springer, Singapore. https://doi.org/10.1007/978-981-19-2689-1_40
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DOI: https://doi.org/10.1007/978-981-19-2689-1_40
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