Early aerodynamic mathematical methods rely on potential flow concepts that formally isolate aerodynamic drag into a profile and an induced drag component. The more recent evolution of Navier–Stokes-based Computational Fluid Dynamics (CFD) methods typically directly computes aerodynamic forces. It does so using surface integration of pressure and viscous forces, which does not readily enable conventional separation of profile and induced drag. Isolating induced drag from aerodynamic drag is not well developed using CFD, leading to the present effort that derives a mathematical framework to extract induced drag from CFD model results. The present approach builds on mass, momentum, and energy equation control volume analysis performed within the CFD results. We find that the energy equation provides the necessary means for the closure of quantifying induced drag within the context of minor assumptions. In addition, the results indicate an interesting character in the development of energy losses in the context of induced drag associated with flow reorganization into a tip vortex. The results from the approach indicate accuracy in the method as displayed with good correlation to predictions from analytical and potential flow methods for a variety of wing planforms. Results indicate a novel and efficient method to extract induced drag from CFD models.

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从计算流体动力学计算诱导阻力的新方法

早期的空气动力学数学方法依赖于潜在的流动概念，这些概念将空气动力阻力正式隔离为轮廓和诱导阻力分量。基于 Navier-Stokes 的计算流体动力学 (CFD) 方法的最新发展通常直接计算空气动力。它使用压力和粘性力的表面积分来实现，这不容易实现轮廓和诱导阻力的传统分离。使用 CFD 没有很好地从空气动力阻力中分离诱导阻力，导致目前的努力是推导出数学框架从 CFD 模型结果中提取诱导阻力。本方法基于在 CFD 结果中执行的质量、动量和能量方程控制体积分析。我们发现能量方程为在次要假设的背景下量化诱导阻力提供了必要的手段。此外，结果表明在与流动重组为尖端涡流相关的诱导阻力的背景下，能量损失的发展具有有趣的特征。该方法的结果表明该方法的准确性与对各种机翼平面的分析和潜在流动方法的预测具有良好的相关性。结果表明，这是一种从 CFD 模型中提取诱导阻力的新型有效方法。该方法的结果表明该方法的准确性与对各种机翼平面的分析和潜在流动方法的预测具有良好的相关性。结果表明，这是一种从 CFD 模型中提取诱导阻力的新型有效方法。该方法的结果表明该方法的准确性与对各种机翼平面的分析和潜在流动方法的预测具有良好的相关性。结果表明，这是一种从 CFD 模型中提取诱导阻力的新型有效方法。