Active flow control (AFC) is conventionally used to reduce flow separation at high angles of attack. A novel alternative form of AFC for controlling rotor blade loads in attached flow is examined. The AFC system employs pulsed fluidic jets near the trailing edge of a VR-12 airfoil on the pressure side and suction side. Each jet has two operating modes: tangential blowing and normal blowing. Unsteady Reynolds-averaged Navier–Stokes simulations are performed to characterize the unsteady aerodynamic phenomena induced by actuation at low and moderate angles of attack. The simulation approach is validated using data from recent low-speed ($M_{\infty }=0.06$) wind-tunnel experiments. The normal blowing modes produce nearly symmetric changes in the lift and moment that are proportional to the relative jet strength. The tangential blowing modes have a minor effect on lift and moment but have a beneficial effect on drag. High-speed simulations, up to $M_{\infty }=0.5$, are also performed to determine the effect of freestream Mach number on actuator performance. Finally, simulations representing rotor blade dynamics during vibrations are carried out to illustrate the effect of unsteadiness associated with blade motion. This is the first instance showing that AFC is a viable approach for potentially controlling rotor vibrations in attached flow.

主动流控制（AFC）通常用于减少高迎角时的流分离。研究了一种新颖的AFC替代形式，用于控制附加流中的转子叶片负载。AFC系统在压力侧和吸力侧的VR-12机翼尾缘附近采用脉冲式射流。每个喷嘴都有两种运行模式：切向吹气和法向吹气。雷诺平均非稳态Navier-Stokes模拟的执行是为了表征在低攻角和中攻角下致动引起的非稳态空气动力学现象。使用最近的低速（${\mathrm{中号}}_{\infty }=0.06$）风洞实验。正常的吹气模式会在升力和力矩上产生几乎对称的变化，与相对射流强度成正比。切向吹气模式对升力和力矩影响不大，但对阻力有有益的影响。高速仿真，最高${\mathrm{中号}}_{\infty }=0.5$也执行，以确定自由马赫数对执行器性能的影响。最后，进行了代表振动过程中转子叶片动力学的仿真，以说明与叶片运动相关的不稳定现象的影响。这是第一个实例，表明AFC是一种可行的方法，可以潜在地控制附加流中的转子振动。