This report covers an experimental investigation of boundary layer transition on a body of revolution at low subsonic speeds, with emphasis placed on the effects of spin and yaw on transition.The methods tried for detecting boundary layer transition for this particular investigation are reviewed and the technique finally adopted, the use of a hot wire anemometer, is described in detail.It was found that at angles of yaw, the transition from laminar to turbulent flow in the boundary layer occurs at a higher Reynolds number over most of the body than at zero yaw, and that spin has a negligible effect on the transition Reynolds number. It was observed however that the effect of spin varies from the front to the rear of the body, although it was not ascertained whether this effect was a result of the influence of the nose section, the tripping device which was used to obtain transition, or a combination of both.
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