TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
Online ISSN : 2189-4205
Print ISSN : 0549-3811
ISSN-L : 0549-3811
Influence of Pre-twist Distribution at the Rotor Blade Tip on Performance during Hovering Flight
Shigeru TAKEDAMasahiko SUGIURAYasutada TANABEHideaki SUGAWARAMasahiro KANAZAKIMasatoshi HARIGAE
Author information
JOURNALS FREE ACCESS

2015 Volume 58 Issue 1 Pages 39-44

Details
Abstract

In this paper, optimization of blade twist distribution to maximize the performance of a rotor during hovering flight is described. The Japan Aerospace Exploration Agency has been developing a hybrid method coupled with computational fluid dynamics (CFD) and a prescribed wake model to reduce the computational cost. In this study, as a first step for the application of this method to optimize the blade configuration, the influence of the blade twist distribution variation on the figure of merit is investigated. The Hover Tip Vortex Structure Test (HOTIS) experiment is used as a calculation model, and the tip Mach number is 0.641. It is found that the result of using the hybrid method for the baseline blade configuration corresponds well with the full CFD of the rotor performance and figure of merit. For the influence of the blade twist on the figure of merit, high figures of merit are obtained when the difference of the blade twist at r/R=0.875 from the baseline Δθ1 is around 1–3 deg and the difference of the blade twist at r/R = 1.0 from the baseline Δθ2 is of negative value. Particularly, in the case of Δθ1 = 2.0 and Δθ2 = −3.7 deg, a maximum value of figure of merit of about 1.5% higher than the baseline design is achieved.

Information related to the author
© 2015 The Japan Society for Aeronautical and Space Sciences
Previous article Next article
feedback
Top