Boundary layer effects on airfoil lift
Name
14173517.pdf
Size
8.79 MB
Format
Adobe PDF
Checksum (MD5)
a1b7193e759abf17d96b9b1da33f8116
Author(s)
Schneider, Kurt H. (Kurt Herbert)
Date Issued
1958
Publisher
Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958]
Series/Report no.
GTL report #47
Abstract
A study of the discrepancy in lift between potential flow calculations and experiments was made. In potential flow the fluid is assumed to follow the contour of the airfoil, forming a stagnation point at the geometric center of the trailing edge. In the flow of a viscous fluid around an airfoil a boundary layer forms along the surface of the airfoil changing its effective shape. The pressure at the trailing edge is approximately equal to the static pressure at upstream infinity. Detail stagnation and static pressure and flow direction surveys were made near the trailing edge on a 50 inch chord NACA 0015 airfoil with trailing edge thickness increased to three per cent chord. By the use of thin airfoil theory, modified to include terms. of second order, good agreement with published experiments in lift and pressure distribution is obtained. Using Teledeltos paper, an electrical analog of the flow around the NACA 0015 airfoil in the tunnel was made. A method was developed for determining velocity directly from the analog.
Description
September 1958
Includes bibliographical references (leaves 48-49)
Persistent DSpace Link
