Abstract
The experiment on aircraft spin phenomena was conducted at the low speed wind tunnel of Nagoya University with its exit test section inclined vertically. The model used in this experiment consists of three parts: a main wing, a fuselage, and a tail. Due to the stability effect of the tail, rotation of the model is decreased at low angles of attack, while it is increased at high angles of attack. As a result of pressure measurements, the horizontal tail wing was found to be the cause of this phenomenon. More specifically, a vortex is created from the leading edge of the windward horizontal tail wing, so that negative pressure regions appear on the windward horizontal wing and the vertical wing.
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