@techreport{oai:jaxa.repo.nii.ac.jp:00043157,
 author = {高木, 俊幸 and Takagi, Toshiyuki},
 month = {Nov},
 note = {Static pressure measurements on the endwalls of a nozzle cascade were made in a single stage, transonic axial-flow turbine with variable nozzles. Tests were conducted at two nozzle-offset-angles, where the theoretical exit Mach numbers were between 0.94 and 1.32. The test results were compared with the solutions of the inviscid, compressible, two-dimensional flow on a blade-to-blade stream surface through a single blade row. Static pressures on the endwalls near the suction-side of the nozzle vane were higher than the calculated values. However, near the pressure-side of the nozzle vane the measured values coincided well with the calculated values. At the throat section there were not many great discrepancies between the measured values and the calculated values. Mini-mum pressure occurred downstream from the throat section between the two nozzle vanes, and thc location changed with exit flow conditions. Periodicity of pressure distributions appeared downstream from the cascade and the exit flow was gradually uniform along the streamlines. Far downstream, the measured pressure distributions were in relatively good agreement with the calculated ones., 資料番号: NALSP0003015, レポート番号: NAL SP-3},
 title = {遷音速環状静止翼列エンドウォール部の圧力分布について},
 year = {1984}
}