@techreport{oai:jaxa.repo.nii.ac.jp:00044991,
 author = {高橋, 侔 and 廣末, 健一 and 宮本, 義人 and 重見, 仁 and 岩崎, 昭人 and 玉置, 元昭 and 織戸, 満紀雄 and 森田, 義郎 and TAKAHASHI, Hitoshi and HIROSUE, Kenichi and MIYAMOTO, Yoshito and SHIGEMI, Masashi and IWASAKI, Akihito and TAMAKI, Motoaki and ORITO, MAKIO and MORITA, YOSHIO},
 month = {Sep},
 note = {An investigation has been conducted to determine the aerodynamic characteristics of the aerodynamic elements of an 8％ subsonic jet transport half model with an upper surface blowing flap system that would augment lift. Wind tunnel tests of leading edge and trailing edge high lift devices were conducted. After investigating those wind tunnel test data, some results were obtained. The set up angles of outer leading edge slats which were divided into three parts were all fixed at 40 degrees. It was determined that the USB flap was a hinged 40-70 type Forward-Main flap and that the inner leading edge had no device because any inner leading edge high lift devices were less effective in augmenting lift. Many data obtained in the wind tunnel tests were offered for the design of the NAL STOL Research Aircraft., 資料番号: NALTR0734000, レポート番号: NAL TR-734},
 title = {STOL実験機半截模型風洞試験(半截模型空力要素の特性)},
 year = {1982}
}