Contributions to the prediction of low Reynolds number aerofoil performance

[摘要] The dominant aspects of low Reynolds number flows are identified and their relevance to aerofoil performance discussed A method for assessing two-dimensional aerofoil performance characteristics, including trailing edge and gross laminar separation, is developed along with a subsidiary direct boundary layer calculation scheme capable of accounting for short laminar separation bubbles The constituent parts of the performance prediction scheme, which consists a vortex panel method with boundary layer corrections and an inviscidly modelled wake, are described in some detail Predictions obtained for both laminar and turbulent separation are also presented For laminar separation, an inviscid Wake Factor Increment correlation is developed to account for the effects of the free laminar shear layers Generally, the predictions of lift and pitching moment may be considered to be within the experimental error, but where this is not the case the applicability of the modelling technique is discussed The developed direct boundary layer calculation technique is demonstrated to provide an indication of the boundary layer growth through a separation bubble for a prescribed pressure distribution whilst encountering no difficulty at separation Comparisons with inverse calculations are made and exhibit good general agreement Finally, the general applicability of the predictive scheme is discussed along with possible future enhancements.

[发布机构] University:University of Glasgow

[关键词] Aerospace engineering, Fluid mechanics