A multidisciplinary research method was employed with the intention to create a series of bio-inspired flattened airfoils, observe their aerodynamic characteristics, and analyse their applicability to small devices or to designs of high-speed trains, within the shortest period in the conceptual stage. A research specimen of a kingfisher, selected for biomimicry, was examined with the following methods: visual inspection, analysis of photographs, manufacturing quality control measurement with a 3D laser scanner, and microscopy. A basic multi-arc-line profile, re-engineered from the overlapped specimen shape data and based on the observations, was used for designing a series of seven derived airfoils. The aerodynamic characteristics of the bio-inspired airfoils were obtained with the panel methods at low and moderate subsonic speeds, while the small transonic difference method was used in the high-subsonic speed range. Basic and ellipse-like airfoils produce higher total drag at low and moderate velocities and higher forebody drag in the high-subsonic range when compared to derived and parabola-like airfoils. The obtained critical Mach numbers are in the range from 0.76 to 0.78, where three bionic airfoils show values equal to or smaller than the values of ellipse- and parabola-like airfoils. The profile with the shortest bio-inspired relative chord has a higher critical Mach number value than the parabola-like profile. The sonic lines above these profiles appear at close positions. The applied set of examination methods of the bio-inspired design is not time consuming and produces sufficiently good results in the conceptual stage. Therefore, a further development of unique and adjusted numerical methods and codes at pre-computational fluid dynamics run is encouraged, together with shape parameterization.

为了在概念阶段的最短时间内创建一系列生物启发的扁平翼型，观察其空气动力学特性并分析其在小型设备或高速列车设计中的适用性，采用了多学科研究方法。通过以下方法检查了被选为仿生动物的翠鸟研究标本：目视检查，照片分析，使用3D激光扫描仪进行制造质量控制测量以及显微镜检查。根据重叠的样本形状数据并基于观察结果，重新设计了基本的多弧线轮廓，以设计一系列七个衍生的机翼。通过面板方法在低和中等亚音速下获得了生物启发型机翼的空气动力学特性，小跨音速差法则用于高亚音速范围。与派生型和抛物线型机翼相比，基本型和椭圆型机翼在低速和中等速度下产生更高的总阻力，在高亚音速范围内产生更高的前体阻力。所获得的临界马赫数在0.76至0.78的范围内，其中三个仿生翼型的值等于或小于椭圆形和抛物线型翼型的值。具有最短的生物启发性相对和弦的轮廓具有比抛物线状轮廓更高的临界马赫数值。这些轮廓上方的声线出现在靠近的位置。应用的生物启发性设计检查方法集不费时，并且在概念阶段可以产生足够好的结果。因此，