On the Experimental Results of the Circular Wing Lattice, Especially with Many Vanes

Abstract

In this paper, the experimental results of the circular wing lattice used with a wind tunnel are described. The wing lattices were formed with 12 and 24 aerofoils, thickness 11%, and setting angle of each wing was 0, ±15, ±30, ±45, ±60, ±75 degrees and under the above condition, the author measured the pressure distribution of the aerofoil along the span and the direction of the stream which flowed from the guide vane. The normal force coefficient, the moment coefficient at the leading edge of the aerofoil, the center of pressure and the moment around the revolution axis which induced the hydrodynamical force were calculated from the pressure distribution. The circulation around each vane, which was calculated from the velocity distribution were compared with one which was calculated from the direction of the surfaces of the aerofoil at the trailing edge, and the inner circulation of the wing lattice, which was calculated from the pressure distribution was compared with one which was calculated from the direction of the stream.