Aircraft directional control effectiveness is analyzed through experiments in wind tunnel. Control surfaces on low aspect ratio lifting surfaces exhibit different lifting capabilities compared to those with high aspect ratio. Such behavior must be carefully considered in the preliminary design phase to avoid any overestimation in size, weight, costs and emissions. Traditional sizing methodologies are based on coupling the effects of the wing planform (e.g. aspect ratio) at low angles of control surface deflection with the effects of wing section (e.g. chord ratio) evaluated on section data in the full range of control surface deflection, so that the non-linear aerodynamics is inherited from 2D data, completely neglecting the different aerodynamic behavior of a low aspect ratio wing at high angles of deflection. To fill this gap, an experimental wind tunnel test campaign on a generic regional turboprop aircraft model with a modular vertical tail with rudder has been performed. Results indicate that the aircraft design methodologies present in public literature underestimate the control surface effectiveness at high angle of deflections by 15% to 25%, leading to an average overestimation of control surface size.

通过风洞实验对飞机的定向控制效果进行了分析。低纵横比提升面上的控制面与高纵横比提升面相比具有不同的提升能力。在初步设计阶段必须仔细考虑这种行为，以避免对尺寸，重量，成本和排放量的任何高估。传统的尺寸确定方法基于将机翼平面形状（例如长宽比）在控制面偏转的低角度下的影响与机翼截面的影响（例如弦比）在整个控制面偏转范围内对截面数据进行评估相结合，因此非线性空气动力学是从2D数据继承而来的，完全忽略了低纵横比机翼在高偏转角时的不同空气动力学行为。为了填补这一空白，已对带有模块化垂直尾舵的通用区域涡轮螺旋桨飞机模型进行了实验性风洞试验。结果表明，公共文献中出现的飞机设计方法将高偏转角时的控制面有效性低估了15％至25％，从而平均高估了控制面尺寸。