Collected Data for Sinusoidal Tests on a NACA 23012 Aerofoil. Volume 2: Pressure Data for a Reynolds Number of 1.5 Million. G.U. Aero Report 8600.

Abstract

Summary: Herein is presented the collected data for tests in which a NACA 23012 aerofoil was subjected to oscillatory displacements in pitch about the quarter chord position. The data clearly illustrates the effect of reduced frequency on the aerofoil characteristics and the chordal pressure distribution at the midspan position of the aerofoil model. The data are presented in two volumes. This volume contains the test data for a Reynolds number of 1.5 x 10 6. For a full introduction and description of test procedure, see volume 1