When
Thursday, April 3, 2025 - 4:00 p.m.
Marlyn Andino
Research Aerospace Engineer
Flow Physics and Control Branch
Research Directorate at NASA’S Langley Research Center
"Active Flow Control Enhanced Aileron of the High-Lift Common Research Model at Takeoff Condition"
AME Lecture Hall, Room S212
Zoom link
Abstract: An experimental investigation was conducted in the NASA Langley 14- by 22-Foot Subsonic Tunnel on the NASA 10% scale High-Lift Common Research Model (CRM-HL) to improve the high-lift aerodynamic performance of the takeoff configuration. Active flow control (AFC) was applied at the aileron hinge line to control flow separation at high aileron deflection angles to increase lift-to-drag ratio (L/D). Improvements in low speed L/D can increase vehicle payload and/or range resulting in a more efficient vehicle. Aileron deflection angles of 0, 7.5, 16, and 25 were investigated. Flow control was applied to the two largest aileron deflections, which are considered the high-lift (HL) improved takeoff configurations. A companion paper will discuss baseline flow characteristics of the CRM-HL at the three takeoff conditions: reference, nominal, and HL-improved. In this paper, we focus on the aerodynamic improvement obtained when AFC was applied to an aileron deflection angle of 16-deg relative to the nominal configuration, an aileron deflection angle of 7.5-deg. Multiple flow control parameters, including actuator type, spacing, and intensity, were investigated to evaluate the efficiency of the actuation system. The different AFC configurations tested were assessed with tuft visualization, steady surface pressure data, and force and moment data. The results indicated that all actuation types and spacings examined led to an increase in lift across the range of angles of attack investigated. Flow separation was mitigated with the injection of momentum at the aileron hinge line. The configurations with the smallest spacing produced the highest improvement in L/D. Steady jet actuation showed higher efficiency but similar aerodynamic performance when compared to the sweeping jet actuators. This work was performed in support of the NASA Advanced Air Transport Technology (AATT) Project.
Bio: Marlyn Andino is a research aerospace engineer in the flow physics and control branch under the Research Directorate at NASA’s Langley Research Center. She currently supports Transonic Truss Brace Wing wind tunnel tests and active flow control activities related to the High-Lift Common Research Model project at NASA Langley. During the course of her career to date at NASA she has played key roles and made significant contributions to the full-scale AFC-enhanced vertical tail technology development jointly sponsored by the NASA Environmentally Responsible Aviation project and Boeing. She was part of the joint NASA/Boeing 757 EcoDemonstrator fight test. She holds a BS in mechanical engineering from the University of Puerto Rico at Mayagüez; a MS in mechanical engineering and a PhD in mechanical and aerospace engineering from Syracuse University. Her primary area of expertise is active flow control (AFC) and fluid dynamics.