Turbulent boundary-layer flow from stationary to moving surfaces.

Abstract

approximation. 3) The pilot pressure distributions together with the distributions of the cross components of the local velocity indicate that the inboard shock wave, starting perpendicularly from the wing surface, extends into the central region (i.e., the region where the influence of both halves of the delta wing is felt). 4) The measurements strongly suggest that the inboard shock wave ends with zero strength in the point where the conical sonic line starts. The way in which this transition occurs has not been clarified by the present measurements. 5) The measurements are in very good agreement with numerical calculations using a shock capturing technique.