@techreport{oai:jaxa.repo.nii.ac.jp:00044198,
 author = {佐藤, 衛 and 神田, 宏 and 須谷, 記和 and 小国, 保男 and 馬場, 滋夫 and 三輪, 等 and 河本, 巌 and 少路, 宏和 and 大竹, 邦彦 and 菊野, 栄次 and 市川, 恵通 and 遠藤, 宏 and 信谷, 英之 and SATO, Mamoru and KANDA, Hiroshi and SUDANI, Norikazu and OGUNI, Yasuo and BABA, Shigeo and MIWA, Hitoshi and KAWAMOTO, Iwao and SHOJI, Hirokazu and OOTAKE, Kunihiko and KIKUNO, Eiji and ICHIKAWA, Yoshimichi and ENDO, Hiroshi and NOBUTANI, Hideyuki},
 month = {Nov},
 note = {Two-dimensional transonic wind tunnel tests of thin airfoils were made as a part of aerodynamic research on propeller blades for advanced turboprop engines. The test airfoils were NACA-16-202 and NACA16-204 which were developed as airfoils for conventional propeller systems at NACA in 1934. The Reynolds number is 8×106. The Mach number was varied from 0.6 to 1.0 and angles of attack from -10 to +16. In addition, vibration characteristics were measured and analyzed., 資料番号: NALTM0615000, レポート番号: NAL TM-615},
 title = {Investigation of ATP blades(PartI): Test of Thin Airfoils in the NAL 2-D Transonic Wind Tunnel},
 year = {1989}
}