Pitching Moment Corrections from Axial Forces on Isolated Ring Wings at Angle of Attack

摘要

The integral equation describing the added moment resulting from axial forces for camber and taper is developed for an isolated ring wing at angle of attack, and is reduced to expressions giving the added moment for ring wings with a circular arc cambered section and the added moment for wing-section taper. Weissinger's results for the circular arc cambered section is extended to a generalized solution for cambered sections of arbitrary shape. The added moment and change in aerodynamic center caused by axial forces are applied to correct the pitching moment and location of aerodynamic center for a cylindrical wing at angle of attack. (Author)