## Abstract

The structure of a laminar supersonic boundary layer is examined near a convex corner, turning the flow through an angle $\alpha $$^{\ast}$, on the assumption that $\alpha $$^{\ast}$Re$^{\frac{1}{4}}$ $\sim $ 1 where Re is the Reynolds number of the flow. In common with related problems already examined, the boundary layer takes on the character of a triple-deck with the initial pressure fall occurring upstream of the corner. Numerical studies show that as $\alpha $$^{\ast}$Re$^{\frac{1}{4}}$ increases so does the proportion of the total pressure fall which occurs upstream of the corner and an analysis is given which strongly suggests that as $\alpha $$^{\ast}$Re$^{\frac{1}{4}}$ $\rightarrow $ $\infty $ the relative pressure fall downstream of the corner vanishes. The theory is carried over to include angles $\alpha $$^{\ast}$ which are small but finite [$\alpha $$^{\ast}$ $\ll $ 1, $\alpha $$^{\ast}$Re$^{t}$ $\gg \ $ 1 for all t > 0] and an earlier theory, due to Matveeva and Neiland, is made uniformly valid and completed. Comparisons with experiment are made which, while not being decisive, are encouraging.