Download or read book A Flight Investigation of the Effect of Shape and Thickness of the Boundary Layer on the Pressure Distribution in the Presence of Shock written by Eziaslav N. Harrin and published by . This book was released on 1952 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in flight at free-stream Mach numbers up to about 0.77 to determine the effect of a laminar boundary layer and thin and thick turbulent boundary layers on the chordwise pressure distribution over an airfoil in the presence of shock at full-scale Reynolds numbers. Boundary-layer and pressure-distribution measurements were made on a short-span airfoil built around ar wing of a fighter plane. Boundary-layer Reynolds numbers (based on momentum thickness and flow parameters at the outer edge of the boundary layer) were about 3,000 for the laminar boundary layer and 10,000 for the thickest turbulent boundary layer with local Mach numbers ranging up to 1.3 and chord Reynolds numbers up to about 21,000,000.