@techreport{oai:jaxa.repo.nii.ac.jp:00044846,
 author = {蓑田, 光弘 and 山崎, 紀雄 and MINODA, Mitsuhiro and YAMAZAKI, Norio},
 month = {Nov},
 note = {The multi-stage high pressure compressor of a turbofan engine has to operate at off-design conditions when the engine runs at very low rotational speeds such as when starting an engine. Therefore it is necessary for a stable operation of an engine to control the high pressure compressor by variable stator vanes and/or bleeding air. The maximum value of the VSV schedule may be over 40deg, but the cascade data were obtained only for so-called operating ranges so little data were available for off-design points. Two-dimensional cascade tests of the inlet guide vane of the blade section NACA 63(10A4K6)10 were made at high angles of attack, up to 55deg. Data were obtained at solidities from 0.75 to 1.5 and at rather low inlet Mach numbers at the axial inlet angle. The tests were done by the wake traverse method using a five-hole Pitot tube. The test results of deviation angles and loss coefficients are given., 資料番号: NALTR0592000, レポート番号: NAL TR-592},
 title = {入口案内翼の2次元翼列実験(正の大迎角をもつ場合)},
 year = {1979}
}