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Advancement of aerofoil section dynamic stall synthesis methods for rotor design

Published online by Cambridge University Press:  27 January 2016

W. Sheng ,
W. Chan  and
R. Galbraith
W. Sheng
Affiliation:
Glasgow University, Glasgow, UK
W. Chan*
Affiliation:
Yeovil, UK
R. Galbraith
Affiliation:
Glasgow University, Glasgow, UK
*
wayland.chan@yahoo.co.uk
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Abstract

Dynamic stall is a complex process encountered by an aerofoil in the unsteady flow environment such as a helicopter rotor in forward flight as well as a fixed wing aircraft in manoeuvres and in other unsteady situations. The onset of dynamic stall effectively determines the flight envelope of the helicopter. Significant effort are being made to develop CFD to capture the dynamic stall behaviour, however traditional engineering models based on lifting line theory still offer fast turn-round and broad understanding required for the rotor design process. This paper describes a new engineering model for dynamic stall, developed originally for wind turbine application at a typical Mach number of 0·12. The new dynamic stall model, with a better definition of stall onset, is based on improvements made to Beddoes’ original trailing edge stall model. This paper will describe and demonstrate the improvements in identifying both the stall-onset and the pitching moment break at high pitch rates, when being applied to a generic rotor aerofoil RAE 9651 at M = 0·3. Further validation against oscillatory tests and other Mach numbers are still required. However the study has provided sufficient confidence for it to be employed in a rotor analysis code.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1179 , May 2012 , pp. 521 - 539
Copyright
Copyright © Royal Aeronautical Society 2012 

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