Lift-Interference and Blockage Corrections for a Two-Dimensional Aerofoil during a Sudden Change of Incidence

摘要

The applicability of standard lift correction formulas to a two-dimensional NACA 0015 airfoil (chord 67 mm, span 100 mm) was demonstrated using a suction-type wind tunnel with variations from open-jet to fully-closed working sections, for velocities of up to 32.6 m/sec (Reynolds number 161,000). However, measurements of static pressures around the airfoil surface are unreliable, variations in the corrected value being an order of magnitude greater than the corrections themselves. Thus no detailed analysis of the pressures during a sudden change of incidence was possible, with no intermediate trend apparent.