@techreport{oai:jaxa.repo.nii.ac.jp:00044667,
 author = {佐々木, 誠 and 高原, 北雄 and 熊谷, 隆王 and SASAKI, Makoto and TAKAHARA, Kitao and KUMAGAI, Takao},
 month = {Jul},
 note = {Coolant flow on a plane model with a cylindrical nose, which simulates the leading edge portion of a film-cooled turbine blade, was studied by means of a visualizing technique. The secondary air injected from rows of blowing holes located near the leading edge of the model was visualized by adding vapor of paraffin into it. The change of the flow pattern of the injected jets was examined and compared with the change of the pressure distribution on the model surface, the blowing characteristics and the change of the film cooling effectiveness reported in the previous paper. When the ratio of the momentum flux of the injected jets to that of the mainstream exceeded a critical value, the jets tended to blow off the surface. This blow-off(lift-off) caused a fall in the film cooling effectiveness near the blowing holes. With injection through holes inclined in the spanwise direction, the surface was covered more effectively and the onset of the blow-off was delayed. The thickness of the injected coolant flow was much greater than that of the boundary layer without injection., 資料番号: NALTR0418000, レポート番号: NAL TR-418},
 title = {タービン翼の前縁部吹出しフィルム冷却に関する基礎実験(Ⅱ)吹出し流れの可視化},
 year = {1975}
}