Framework for the Optimisation of a Helicopter Rotor Blade with an Approximate BERP Tip

Johnson, Catherine S.; Woodgate, M.; Barakos, George N.

doi:10.1002/9781118928691.ch10

Cited by 1 publication

(1 citation statement)

References 24 publications

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“…local shifts of the blade cross-section in tangent and normal directions with respect to the blade-chord plane. It should be underlined that a shape of a blade tip has significant influence on main rotor performance, which is discussed in Johnson et al (2017a, 2017b).…”

Section: Performance Optimisation Of Main Rotor In Hovermentioning

confidence: 99%

Performance improvement of helicopter rotors through blade redesigning

Stalewski

Zalewski

2019

AEAT

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Purpose The purpose of this paper is to determine dependencies between a rotor-blade shape and a rotor performance as well as to search for optimal shapes of blades dedicated for helicopter main and tail rotors. Design/methodology/approach The research is conducted based on computational methodology, using the parametric-design approach. The developed parametric model takes into account several typical blade-shape parameters. The rotor aerodynamic characteristics are evaluated using the unsteady Reynolds-averaged Navier–Stokes solver. Flow effects caused by rotating blades are modelled based on both simplified approach and truly 3D simulations. Findings The computational studies have shown that the helicopter-rotor performance may be significantly improved even through relatively simple aerodynamic redesigning of its blades. The research results confirm high potential of the developed methodology of rotor-blade optimisation. Developed families of helicopter-rotor-blade airfoils are competitive compared to the best airfoils cited in literature. The finally designed rotors, compared to the baselines, for the same driving power, are characterised by 5 and 32% higher thrust, in case of main and tail rotor, respectively. Practical implications The developed and implemented methodology of parametric design and optimisation of helicopter-rotor blades may be used in future studies on performance improvement of rotorcraft rotors. Some of presented results concern the redesigning of main and tail rotors of existing helicopters. These results may be used directly in modernisation processes of these helicopters. Originality/value The presented study is original in relation to the developed methodology of optimisation of helicopter-rotor blades, families of modern helicopter airfoils and innovative solutions in rotor-blade-design area.

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Section: Performance Optimisation Of Main Rotor In Hovermentioning

confidence: 99%