Online from: 1929
Subject Area: Mechanical & Materials Engineering
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|Title:||Correlation of helicopter rotor aeroelastic response with HART-II wind tunnel test data|
|Author(s):||A. Arun Kumar, (Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India), S.R. Viswamurthy, (Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India), R. Ganguli, (Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India)|
|Citation:||A. Arun Kumar, S.R. Viswamurthy, R. Ganguli, (2010) "Correlation of helicopter rotor aeroelastic response with HART-II wind tunnel test data", Aircraft Engineering and Aerospace Technology, Vol. 82 Iss: 4, pp.237 - 248|
|Keywords:||Aerodynamics, Flow, Helicopters, Vibration measurement|
|Article type:||Research paper|
|DOI:||10.1108/00022661011082713 (Permanent URL)|
|Publisher:||Emerald Group Publishing Limited|
|Acknowledgements:||The authors thank Dr Berend G. Van der Wall, DLR, for providing them with the HART-II data.|
Purpose – This paper aims to validate a comprehensive aeroelastic analysis for a helicopter rotor with the higher harmonic control aeroacoustic rotor test (HART-II) wind tunnel test data.
Design/methodology/approach – Aeroelastic analysis of helicopter rotor with elastic blades based on finite element method in space and time and capable of considering higher harmonic control inputs is carried out. Moderate deflection and coriolis nonlinearities are included in the analysis. The rotor aerodynamics are represented using free wake and unsteady aerodynamic models.
Findings – Good correlation between analysis and HART-II wind tunnel test data is obtained for blade natural frequencies across a range of rotating speeds. The basic physics of the blade mode shapes are also well captured. In particular, the fundamental flap, lag and torsion modes compare very well. The blade response compares well with HART-II result and other high-fidelity aeroelastic code predictions for flap and torsion mode. For the lead-lag response, the present analysis prediction is somewhat better than other aeroelastic analyses.
Research limitations/implications – Predicted blade response trend with higher harmonic pitch control agreed well with the wind tunnel test data, but usually contained a constant offset in the mean values of lead-lag and elastic torsion response. Improvements in the modeling of the aerodynamic environment around the rotor can help reduce this gap between the experimental and numerical results.
Practical implications – Correlation of predicted aeroelastic response with wind tunnel test data is a vital step towards validating any helicopter aeroelastic analysis. Such efforts lend confidence in using the numerical analysis to understand the actual physical behavior of the helicopter system. Also, validated numerical analyses can take the place of time-consuming and expensive wind tunnel tests during the initial stage of the design process.
Originality/value – While the basic physics appears to be well captured by the aeroelastic analysis, there is need for improvement in the aerodynamic modeling which appears to be the source of the gap between numerical predictions and HART-II wind tunnel experiments.
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