The work presented in this paper is a culmination of a multiyear joint experimental and computational effort to explore the feasibility of using active flow control (AFC) on a simple hinged flap system for recovering lift comparable to a conventional high-lift system consisting of Fowler flaps. The baseline configuration chosen for this work is the high-lift version of the NASA Common Research Model (CRM), which is a representative modern aircraft consisting of wing, fuselage, nacelle/pylon, slats, Fowler flaps, and slat and flap brackets. A simplified high-lift (SHL) system was created by replacing the Fowler flaps and flap brackets with a simple hinged flap system equipped with integrated modular AFC cartridges on the suction surface of the flap shoulder, and the resulting geometry is known as the CRM–SHL–AFC configuration. Parametric studies were conducted in the earlier phases of this effort to numerically evaluate and downselect the more efficient AFC designs for wind-tunnel tests. These simulations were performed with the PowerFLOW^® code, which is a lattice-Boltzmann-based computational fluid dynamics code. Good agreement was reported in a previous paper between the numerical results and the experimental data for the lift characteristics of the CRM–SHL–AFC configuration as a function of actuation levels at the nominal landing conditions. The current effort is focused on demonstrating the applicability of the PowerFLOW code for predicting the aerodynamic performance of the conventional and the AFC-enabled simplified high-lift CRM configurations for a broad angle of attack range, including maximum lift conditions.

本文提出的工作是多年联合实验和计算工作的结晶，旨在探索在简单的铰链襟翼系统上使用主动流量控制 (AFC) 恢复升力的可行性，该系统可与由福勒襟翼组成的传统高升力系统相媲美. 为这项工作选择的基线配置是 NASA 通用研究模型 (CRM) 的高升力版本，这是一种具有代表性的现代飞机，由机翼、机身、短舱/挂架、缝翼、福勒襟翼以及缝翼和襟翼支架组成。一个简化的高升力 (SHL) 系统是通过用一个简单的铰链襟翼系统替换 Fowler 襟翼和襟翼支架来创建的，该系统在襟翼肩部的吸力面上配备了集成的模块化 AFC 滤芯，由此产生的几何形状被称为 CRM– SHL-AFC 配置。在这项工作的早期阶段进行了参数研究，以对风洞测试更有效的 AFC 设计进行数值评估和选择。这些模拟是使用 PowerFLOW 进行的^®代码，这是一种基于格子玻尔兹曼的计算流体动力学代码。在之前的一篇论文中，CRM-SHL-AFC 配置的升力特性作为标称着陆条件下的驱动水平的函数的数值结果和实验数据之间报告了良好的一致性。目前的工作重点是展示 PowerFLOW 代码的适用性，用于预测常规和启用 AFC 的简化高升力 CRM 配置的空气动力学性能，以适应广泛的攻角范围，包括最大升力条件。