増速翼列に適する翼型の研究 : (第2報)好適な翼型の翼列実験

抄録

The wind tunnel tests have been carried out on the profile specially designed by our theoretical method described in Report 1, and arranged in the lattice condition of pitchchord ratio t/l=1.0 and lattice angle θ₁=150° so as to examine the reliability of the theoretical method. The polar diagram of our profile seems to be slightly superior to that of Clark Y, and besides, the pressure center of the former is almost immovable throughout the range of C_a=0.3∼1.5. Further, the surface pressure distribution of the profile at the aimed lift coefficient has been proved to coincide, as it was expected, fairly well with the prescribed theoretical one.