joined wing aircraft, swept back wing, swept forward wing, horizontal tail wing, six component measurement, wing tip separation, low speed wind tunnel, visualization test, lift to drag ratio
その他のタイトル（英）
Low-speed wind tunnel tests on the joined-wing aircraft models
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
National Aerospace Laboratory Advanced Aircraft Research Group
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所資料
雑誌名(英)
Technical Memorandum of National Aerospace Laboratory
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.
後退・前進翼型結合翼機の低速風洞試験
naltm00695.pdf
(3.71MB)
