Abstract
This chapter discusses leading-edge flow separation. The separation of flow at the leading edge may influence the whole flow regime over a surface. At the leading edge, similar to the other cases of separation, because of the adverse pressure gradient, the viscous flow separates. Another subject of interest is leading-edge flow separation on a spike protruding in front of a blunt nose at supersonic speeds. Such a spike may be gainfully applied for a high-speed aircraft, reducing the drag and heat transfer rate. It can be used as an effective control device. The chapter discusses the subject of the leading-edge separation at subsonic speeds and the same subject at supersonic velocities. McGregor's theory on the leading-edge separation is based upon the balance of energy of the standing eddy downstream of the short bubble.
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