@techreport{oai:jaxa.repo.nii.ac.jp:00044228,
 author = {藤田, 敏美 and 岩崎, 昭人 and 藤枝, 郭俊 and 滝澤, 直人 and FUJITA, Toshimi and IWASAKI, Akihito and FUJIEDA, Hirotoshi and TAKIZAWA, NAOTO},
 month = {Mar},
 note = {菱形結合翼機の直接横力制御における横力と操舵角余裕の増大のため上翼を採用した。風洞試験では,水平尾翼翼幅が主翼翼幅の60％の菱形結合翼機を用いた。上翼は後縁舵面を持ち,主翼翼幅の60％位置に垂直に設置した。試験で用いた4つの上翼は,異なる面積と縦横比を持ち,それらの二つはNACA0012翼型で,他の二つはEC1040翼型である。試験結果は,主翼前縁または主翼前方に張りだした上翼が直接横力制御に効果的であり,また大きな縦横比が横力を得るために有利であることが示された。, Low-speed wind tunnel tests were conducted on a diamond shaped joined-wing airplane model employing an upper fin system and having a wing span ratio (rear/front wing) of 0.60. The control surface was located at the trailing edge portion of the upper fin which are vertically situated at 60% spanwise location of the front wing. Four upper fins were tested, each having a different wing area and aspect ratio. Two fins used the NACA0012 wing section and two the EC 1040 wing section. Results indicate that an upper fin installed at the front wing leading edge or an over hanging upper fin are most effective for obtain direct side-force. In addition, the larger aspect ratio of these fin configurations was found to be superior to the gain of the side-force., 資料番号: NALTM0645000, レポート番号: NAL TM-645},
 title = {菱形結合翼機の上翼舵面による直接横力制御力の低速風洞試験},
 year = {1992}
}