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Unsteady flow around helicopter rotor blade sections in forward flight

Published online by Cambridge University Press:  04 July 2016

S. T. Shaw and
N. Qin
S. T. Shaw
Affiliation:
College of AeronauticsCranfield UniversityBedford, UK
N. Qin
Affiliation:
College of AeronauticsCranfield UniversityBedford, UK
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Abstract

The aerodynamic performance of aerofoils performing unsteady motions is important for the design of helicopter rotors. In this respect the study of aerofoils undergoing in-plane oscillations (translation along the horizontal axis) provides useful insight into the flow physics associated with the advancing blade in forward flight. In this paper a numerical method is developed in which the unsteady thin layer Navier-Stokes equations are solved for aerofoils performing rigid body motions. The method has been applied to the calculation of the flowfield around a NACA 0012 aerofoil performing in-plane motions representative of high-speed forward flight. Comparison of computed pressure data with experimental measurements is generally found to be good. The quantitative differences observed between computations and experiment are thought to have arisen mainly as a consequence of the low aspect ratio of the model rotor employed in the windtunnel tests.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1019 , January 1999, pp. 35 - 44
Copyright
Copyright © Royal Aeronautical Society 1999 

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