【摘要】 随着绿色航空对节能减排需求的日益迫切，发展高效的湍流减阻技术已成为飞行器设计的关键课题，而微肋条技术的工程化应用亟须一套快速可靠的评估与模拟体系。为发展适用于工程实际的微肋条表面减阻快速评估与高精度数值模拟方法，本文提出了一套系统的减阻效果评估与模化框架。该评估方法基于实验数据的经验关系，通过读取壁面剪切应力与边界层内特定高度处的横流角，实现了对全机身微肋条表面经验减阻率的快速预测。同时，提出并验证了基于k-ω SST湍流模型壁面ω值修正的模化方法，通过引入减阻模化因子入，并建立其与当地第一层网格无量纲高度y~+及模化减阻率之间的定量关系，可在仿真中有效复现微肋条的物理减阻效果。针对光机身模型，在不同马赫数（0.2～0.785）下，模化减阻率与经验减阻率吻合良好，最大相对误差低于0.2%；在变迎角工况下，该方法能合理反映横流角对减阻效果的削弱影响，模化相对误差仍可控制在6.2%以内，该精度满足工程应用需求。为微肋条减阻技术在飞行器设计中的快速效能评估与数值仿真应用提供了可靠的工具。更多还原

【Abstract】 With the growing demand for energy conservation and emission reduction in green aviation, developing high-efficiency turbulent drag reduction technology has become a key issue in aircraft design, as the engineering application of riblets urgently calls for a fast and reliable evaluation system. This paper aims to develop a robust and efficient methodology for evaluating and numerically modeling the drag reduction performance of micro-riblet configurations in engineering applications. A simplified clean fuselage model was employed, and numerical simulations were conducted using the threedimensional, compressible RANS equations with the SST k-ω turbulence model. The evaluation method, grounded in an empirical database, rapidly predicts the theoretical drag reduction rate across the entire fuselage by processing local wall shear stress and the flow yaw angle within the boundary layer. For the modeling approach, a drag reduction modeling factor λ is introduced, which modifies the wall value in the turbulence model. A key innovation is establishing a quantitative relationship for λ based on the local dimensionless grid height y~+ and the theoretical drag reduction rate, implemented using an explicit function fit for the y~+ dependence and piecewise linear interpolation for the drag reduction rate dependence to enhance robustness over traditional power-law fits. The results demonstrate that the modeled drag reduction rate agrees exceptionally well with theoretical predictions across a range of Mach numbers(0.2 to 0.785), with a maximum error of less than 0.2%. The piecewise interpolation strategy effectively mitigated significant errors observed with traditional fits at high y~+ conditions. Under varying angles of attack, the method successfully captured the detrimental effect of increased flow yaw angle, with modeling error remaining within 6.2%. It provides a comprehensive, accurate, and robust framework for the assessment and numerical simulation of micro-riblet drag reduction, offering a valuable tool for aerodynamic optimization in engineering design.更多还原