Dynamic similar models are designed to study the flight behavior of the full-scale aircraft in early design stages. Due to physical and operational constraints, full dynamic similarity between the scaled-down model and full-scale aircraft is not feasible. Thus, the scale model would be flying at different Reynolds number and Mach number. A given aircraft configuration with specific aerodynamic characteristics will have different performance if Mach number and Reynolds number are changed considerably, which results in different dynamic behavior of the scale model. To compensate for these dissimilarities, it is proposed to modify the airfoil geometry of the scale model to preserve aerodynamic similarity. In this study, based on the flight regime and design requirements, maximum thickness of the airfoil, maximum camber, and their respective location are modified to preserve aerodynamic characteristics at different Mach and Reynolds numbers. Geometry optimization was performed using Particle Swarm Optimization and the geometry optimization results show that it is possible to mitigate the change in Reynolds and Mach number in various flight conditions. It has been shown that optimized geometries of all test cases had airfoils with lower maximum thickness and slightly higher maximum camber.

动态相似模型旨在研究全尺寸飞机在早期设计阶段的飞行行为。由于物理和操作限制，缩小模型和全尺寸飞机之间的完全动态相似性是不可行的。因此，比例模型将以不同的雷诺数和马赫数飞行。如果马赫数和雷诺数发生较大变化，则具有特定气动特性的给定飞机构型将具有不同的性能，从而导致比例模型的动力学行为不同。为了补偿这些差异，建议修改比例模型的翼型几何形状以保持空气动力学相似性。在这项研究中，根据飞行状态和设计要求，翼型的最大厚度、最大外倾角、以及它们各自的位置被修改以保持不同马赫数和雷诺数下的空气动力学特性。使用粒子群优化进行几何优化，几何优化结果表明可以减轻各种飞行条件下雷诺数和马赫数的变化。已经表明，所有测试用例的优化几何结构具有较低的最大厚度和稍高的最大外倾角的翼型。