ボルテックス·フラップ付きデルタ翼の静的ロール特性について

抄録

Static normal force and rolling moment measurements for 60° and 70° delta wings with vortex flaps have been done for different roll angles at a Reynolds number based on a centerline chord of 1.3×10⁵. Smoke visualization tests have also been done. Results show that the 60° delta wing is statically unstable in roll at the angle of attack of 35° when vortex flaps were deflected 30° downward. This is because the chordwise position where the vortex breakdown occurs is different for the left and right wings when in roll. The 70° delta wing with vortex flaps possesses static roll stability. Static rolling moment hysteresis has been observed for the 60° delta wing with a flap deflection angle of 30° at an angle of attack of 45°.