@techreport{oai:jaxa.repo.nii.ac.jp:00039810,
 author = {藤枝, 郭俊 and 伊藤, 婦美子 and 岩崎, 昭人 and 藤田, 敏美 and 滝澤, 直人 and Fujieda, Hirotoshi and Ito, Fumiko and Iwasaki, Akihito and Fujita, Toshimi and Takizawa, Naoto},
 month = {Jul},
 note = {上反角の無い、後退角付き主翼に前進角と下反角を有する水平尾翼を結合した結合翼機の空力特性を調べるために低速風洞試験を実施した。さらに後退角付き主翼の翼端剥離を遅らせるために、主翼前縁下面を丸棒を利用した簡易な整形を行い、その効果を確認する試験をした。水平尾翼幅が大きくなると上反角効果が不安定になるが、主翼が後退角のみで上反角が無い場合、上反角のある場合に比較し上反角効果はより不安定側に大きい。そして、主翼と水平尾翼の結合方法および水平尾翼翼幅が機体空力特性に大きな影響を与えることなどがわかった。また、主翼前縁下面を丸棒を利用した簡易な整形により翼端剥離が約5度遅くなり、最大揚力が増大し、揚抗比および機体全体の空力特性の改善が確認された。, This report describes the aerodynamic characteristics of the joined wing aircraft obtained by low-speed wind tunnel tests. The joined-wing aircraft consists of a swept-back (40 deg sweep angle at 25 percent chord line) main wing without a dihedral angle (0 deg) and a swept-forward horizontal tail wing (-25 deg sweep angle at 25 percent chord line) with a hedral angle of -22 deg. The tests were conducted on four types of joined-wing aircraft models. For three configurations, the ratios of horizontal tail to main wing span were employed 40 percent, 60 percent and 100 percent, respectively and the leading edge at the tip of horizontal tail was joined to the trailing edge of the main wing. In the other model, the tip of the horizontal tail with the 100 percent ratio and the main wing tip were overlapped. In addition, in order to delay the tip separation of the wing, the leading edge of the main wing of four models were improved simply by using a cylindrical bar and the effects were examined. The results indicated that the dihedral effect becomes unstable as the horizontal tail span increases and that the configuration in which the leading edge of the horizontal tail tip were joined to the wing with no overlap had better aerodynamic characteristics than the configuration with overlap. The spanwise joint location of horizontal tail significantly influenced the aerodynamic characteristics of the joined-wing aircraft. By improving the leading edge of the wing, the separation of wing tip delayed the attack angle by about 5 deg and the maximum lift coefficient and lift-to-drag ratio increased., 資料番号: AA0000673000, レポート番号: NAL TM-695},
 title = {後退・前進翼型結合翼機の低速風洞試験},
 year = {1996}
}