Experimental Work on Unsteady Helicopter Rotor Hub Wakes

Authors

  • Iskandar Shah Ishak School of Mechanical Engineering, Faculty of Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Shuhaimi Mansor School of Mechanical Engineering, Faculty of Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Tholudin Mat Lazim School of Mechanical Engineering, Faculty of Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Shabudin Mat School of Mechanical Engineering, Faculty of Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Mohd Zarhamdy Md. Zain School of Mechanical Engineering, Faculty of Engineering, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Rizal Effendy Mohd Nasir Faculty of Mechanical Engineering, Universiti Teknologi MARA, Malaysia
  • Zurriati Mohd Ali Faculty of Mechanical Engineering, Universiti Teknologi MARA, Malaysia

Keywords:

dynamic analysis, helicopter, tail shake, unsteady aerodynamic, wake

Abstract

Helicopter tail shake phenomenon is a topic of main distress for the rotorcraft industry since it adversely affects the overall performance, occupants’ comfort and handling qualities of helicopter. This research work is intended to investigate the unsteady aerodynamic wake characteristics induced by the helicopter rotor hub that lead to this tail shake phenomenon by executing a wind tunnel campaign. The experiments were carried out in the UTM wind tunnel with a test section of 2m (width) x 1.5m (height) x 5.8m (length) with the maximum wind speed of 80m/s. Dynamic pressure measurements inside the wake due to the effect of helicopter advance ratios and pylon configurations were performed. The dynamic analysis conducted through the power spectral density and root-mean-square methods, has successfully managed to quantify the frequency and the amplitude of unsteadiness of the hub wakes that lead to the tail shake problem. The analyses tell that by employing pylon to the rotor hub, it could significantly reduce the wake unsteadiness up to 99.31%. Subsequently the findings of this research have potential to minimize this long running problem that undoubtedly could benefit the entire growing helicopter industry.

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Published

2020-12-25

How to Cite

Ishak, I. S. ., Mansor, S. ., Mat Lazim, T. ., Mat, S. ., Md. Zain, M. Z. ., Mohd Nasir, . R. E. ., & Mohd Ali, Z. . (2020). Experimental Work on Unsteady Helicopter Rotor Hub Wakes. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 65(2), 314–323. Retrieved from https://www.akademiabaru.com/submit/index.php/arfmts/article/view/2799

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