Abstract
The comprehensive measurements on many different aerofoils made by Pollentz, Page and Levy, as well as later measurements, are reviewed. Then an empirical law is proposed to predict the normal force fluctuations on aerofoils with trailing-edge separations at subsonic speeds from C L — α curves. It is based on an equivalent separation position as deduced from the Kirchoff free-streamline flow for flat plates. The law is developed from the concept of bubble similarity and can also be extended to aerofoils with leading-edge separations if the reattachment position is known. It predicts that the maximum level of normal force fluctuations will be higher for a leading-edge separation than for a trailing-edge separation: this is in accord with the limited experiments available. Some suggestions are made for further research to investigate the application of these laws to modern aerofoils and two-dimensional high lift configurations.
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