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AIAA JOURNAL 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.A turbulent boundary-layer flow from along a fixed surface and on to a moving surface is described and analyzed. Analysis of experimentally measured velocity profiles is used to justify the use of the boundary-layer equations in this flow situation. A calculation technique for moving wall boundary layers based on the Cebeci-Smith method is presented. A new correlation for eddy viscosity in the outer layer suitable for use with the moving wall analysis is given. This correlation is based on the average shear velocity and the boundary-layer thickness. Experimental data of streamwise minimum boundary-layer velocities and a velocity profile presented compare favorably with the calculation technique. Based on the experimental data available it is concluded that the boundary-layer equations are applicable to the flow situation and the calculation technique is satisfactory. Nomenclature/ = dimensionless stream function k j, k 2 = constants in eddy-viscosity formulas P = dimensionless pressure R e = Reynolds number, V e 0/v U e = external flow velocity U t = external flow velocity along the stationary wall U p -wall velocity u,v -x and y components of velocity, respectively A 6 Y] = friction velocity (i/p) 1/2 = average absolute friction velocity in the outer layer -VJV. -integral boundary-layer thickness = boundary-layer thickness = transformed y coordinate = momentum boundary-layer thickness = kinematic viscosity = density = shear stress Subscripts e = outer edge of boundary layer w = wall p = moving wall _ = beginning of moving wall (underline) Downloaded by UNIVERSITY OF ARIZONA on February 4, 2015 | http://arc.aiaa.org |

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