The bird strike incident is a hazard that affects the structural integrity of the aircraft. Bird strikes cause a surge on the wing profile affecting the aerodynamic performances and flight safety of the aircraft. Flight authorities enforce the manufacturers to perform numerous tests before the aircraft are available in the aviation market. Numerical studies and bird strike simulations have become an essential part of aircraft components design to avoid frequent costly tests. The bird strike incidents have been widely studied by numerous researchers as numerically, although only a few considered the effect of bird strike deformation on flow and aerodynamic conditions of an aircraft component. Therefore, this paper aims to present a Computational Fluid Dynamics (CFD) analysis for the aerodynamic behavior of a damaged wing due to a bird strike. To obtain a deformed wing profile for the CFD analysis, the bird strike analysis is performed using Smoothed Particle Hydrodynamics (SPH) for the bird model. Then the deformed airfoil geometry is imported to the CFD solver to obtain the lift, drag, and moment coefficients. The drag coefficient of the deformed wing profile increases due to the pressure distribution disruption of the deformed airfoil. The lift coefficient is also affected by the bird strike but varies with changing angles of attack ($\alpha$). Similarly, the deformed wing profile delivers an impaired coefficient of the moment for smaller angles of attack, reaching a negative value.

鸟击事件是影响飞机结构完整性的危险。鸟击会在机翼轮廓上引起喘振，从而影响飞机的空气动力性能和飞行安全。飞行当局要求制造商在飞机进入航空市场之前执行许多测试。数值研究和鸟类撞击仿真已成为飞机零部件设计的重要组成部分，以避免频繁的昂贵测试。尽管只有少数人考虑了鸟击变形对飞机部件的流动和空气动力学条件的影响，但许多研究人员已对鸟击事件进行了广泛的数值研究。因此，本文旨在针对因鸟击而损坏的机翼的空气动力学行为提出一种计算流体动力学（CFD）分析。为了获得用于CFD分析的变形机翼轮廓，对鸟类模型使用平滑粒子流体动力学（SPH）进行了鸟类打击分析。然后将变形的机翼几何形状导入到CFD求解器中，以获得升力，阻力和力矩系数。变形机翼轮廓的阻力系数由于变形翼型的压力分布破坏而增加。升力系数也受鸟击的影响，但随着迎角的变化而变化（变形机翼轮廓的阻力系数由于变形翼型的压力分布破坏而增加。升力系数也受鸟击的影响，但随着迎角的变化而变化（变形机翼轮廓的阻力系数由于变形翼型的压力分布破坏而增加。升力系数也受飞鸟撞击的影响，但随着迎角的变化而变化（$\alpha$）。同样，变形的机翼轮廓在较小的迎角下传递的力矩系数受损，达到负值。