@techreport{oai:jaxa.repo.nii.ac.jp:00041300,
 author = {齊藤, 喜夫 and 岩崎, 昭人 and 藤田, 敏美 and 藤枝, 郭俊 and 松田, 幸雄 and 菅原, 昇 and 遠藤, 征紀 and Saito, Yoshio and Iwasaki, Akihito and Fujita, Toshimi and Fujieda, Hirotoshi and Matsuda, Yukio and Sugahara, Noboru and Endo, Masanori},
 month = {Jul},
 note = {20-21 May 1999 (62nd). 25-26 Nov. 1999 (63rd), 20-21 May 1999 (62nd). 25-26 Nov. 1999 (63rd), 航空宇宙技術研究所において考案し、概念検討を実施した高速垂直離着陸(VTOL)輸送機の成立性を確認するため、想定した実用機の5%模型による初期の風洞試験を開始した。この輸送機の機体はカナード、チップフィン形式で、胴体中央部の左右に各3基の垂直離着陸用リフトファンを、機体後部に2基の巡航用ファンを配置した。エンジン・システムは次世代輸送機用に開発したコア・エンジンを基本とした。これまでの試験で、概念を確実なものとするために必要な、機体の空力特性の概略、風洞試験上の問題点、遷移飛行に必要なエンジンの要求性能などについての基礎的なデータを得た。しかし、試験中の模型の観察からチップフィン形式の機体の方向安定に問題があったことが認められ、機体形状は再考する必要がある。, In order to confirm the feasibility of practical application of a high speed Vertical Takeoff and Landing (VTOL) passenger transport which was designed and studied conceptually at National Aerospace Laboratory, an initial wind tunnel test was started using a five percent scale model of the passenger transport designed practically. The fuselage of the aircraft was canard- and chip fin-type. Three lift fans each at both sides around the center of the fuselage were arranged for vertical takeoff and landing, and two cruise fans were at the rear of the fuselage. The engine system was based on the core engine which was developed for the next generation passenger transport. The fundamental data were obtained on the outline of the aerodynamic characteristics of the fuselage, the critical issues of the wind tunnel test, and the performance level required for the engine for transition flight, which were necessary for the practical application of the concept. However, from the observation of the model in the course of the test, the directional instability in the fuselage of chip fin-type was revealed, so that the shape of fuselage must be reconsidered., 資料番号: AA0028634015, レポート番号: NAL SP-45},
 title = {高速VTOL輸送機模型の風洞試験},
 year = {2000}
}