Abstract
Summary
A numerical panel method has been developed for the calculation of the two-dimensional potential flow about an aerofoil-spoiler configuration undergoing periodic motions. The cases investigated include a spoiler oscillating in simple harmonic motion on a steady aerofoil, and an aerofoil-spoiler configuration oscillating in overall pitch and normal translation.
The method is a perturbation method about the steady in viscid flow model of an aerofoil-spoiler configuration.
Elements of linear piecewise vorticity are placed on the aerofoil and spoiler surfaces, while the separation streamlines are replaced by elements of uniform vorticity. Time varying vorticities are shed from the spoiler tip and aerofoil trailing edge, along the upper and lower separation streamlines respectively, through the wake closure region, combining in a planar wake downstream of the wake region.
Predicted forces and moments are broadly in agreement with trends of experimental results available in the literature.
Publisher
Cambridge University Press (CUP)
Cited by
2 articles.
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