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.
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
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