The laminar boundary-layer development near the nose of a body of revolution and a two-dimensional airfoil is investigated until the onset of leading-edge separation. This is accomplished through the use of a coordinate transformation which eliminates any geometrical singularity at the nose in the governing boundary-layer equations. The resulting equations are examined by both asymptotic and numerical means. Comparable cases for the three-dimensional body of revolution and the two-dimensional airfoil ...
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