極超音速流中に置かれた凹壁面上の剥離に関する研究

抄録

To clarify the action of the rudder of HSTs, a hypersonic concave flow separation was studied. In hypersonic flows the rudder can not act efficiently because of the boundary layer separation, so that studies of that are needed. In previous studies, the hypersonic concave flow separation was studied to clarify the mechanisms of the separation region. But, the relation between the separation point location and the rudder angle was not cleared. Therefore, experimental and analytical studies were carried out to clarify this relation. The first, the flow visualization experiment by schlieren method was carried out. Then the transfer of the separation point due to the variation of the rudder angle was observed. Next, the separation point transfer in the boundary layer was calculated analytically by potential flow theory. The analytical result agreed well with the experimental observation. Consequently, the correlation between the separation point transfer and the rudder angle variation was confirmed.