aerodynamics, wing rock, delta wing, phase plane method, high angles of attack, rolling motion, free to roll method, vortex, energy transfer, angular momentum, limit cycle
その他のタイトル（英）
Wing rock of delta wings with an analysis by the phase plane method
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
Experimental investigation of the rolling motion of thin delta wings with varying sweep angles, using a free-to-roll method was conducted. The boundaries of dynamically stable and unstable regions of the delta wings were obtained and compared with vortex symmetry and vortex burst curves on a plane of angle of attack of the roll axis vs. delta wing sweep angle. An analytical expression of the rolling moment using a phase plane method was found to be satisfactory for generating the limit cycle similar to the one experimentally obtained. Using this expression, energy transfer in the unsteady motion was calculated.
デルタ翼のウイングロックと相平面法による解析
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