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A comparative assessment of vibration control capabilities of a L-shaped Gurney flap.
- Source :
- Aeronautical Journal; Nov2016, Vol. 120 Issue 1233, p1812-1831, 20p
- Publication Year :
- 2016
-
Abstract
- This work presents the capabilities of a novel L-shaped trailing-edge Gurney flap as a device for vibration reduction. The primary effect of this L-tab is represented by a modification of the reference aerofoil mean line shape through by two counter-rotating vortical structures created at the trailing edge. The comparison of the aerodynamic loads generated by the novel L-tab Gurney flap and a classical trailing-edge flap allows to estimate the ranges of reduced frequency where the L-tab is expected to perform better than a trailing edge flap and vice versa. Linear aerostructural models for a typical section representative of a helicopter blade equipped with a partial-span L-tab or a trailing-edge flap are built, and a higher harmonic control algorithm is applied. Performance are compared between the two devices to reduce separately the N/rev harmonics of the blade root rotating frame vertical force, flapping and feathering moments. The attainment of similar results with classical trailing-edge device is a further confirmation of the potential feasibility of this novel L-tab as an effective alternative means for vibration reduction on rotor blades. [ABSTRACT FROM PUBLISHER]
Details
- Language :
- English
- ISSN :
- 00019240
- Volume :
- 120
- Issue :
- 1233
- Database :
- Supplemental Index
- Journal :
- Aeronautical Journal
- Publication Type :
- Academic Journal
- Accession number :
- 119732331
- Full Text :
- https://doi.org/10.1017/aer.2016.109