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March 26, 2026The Proceedings of Mechanical Engineering Congress JapanOpen Access

Effect of a Leading-Edge Plasma Actuator on the Flow Field around a NACA0012 Airfoil at High Angle of Attack

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Authors

HNHayate NorimotoTYTakafumi Yamada

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Overview

Wind tunnel experiments demonstrate enhanced lift with a plasma actuator on an airfoil, suggesting new flow control methods.

Key Points

  • The research aims to explore how a plasma actuator affects airflow and lift on a NACA0012 airfoil at various angles of attack.
  • Conducted wind tunnel experiments at a flow speed of 5 m/s
  • Measured surface pressure distributions at angles of attack from 0° to 18°
  • Assessed lift variations in pre-stall and post-stall regimes
  • Planned flow visualization for mechanism clarification
  • The actuator increased lift by improving negative pressure on the airfoil's upper surface
  • Significant differences observed between pre-stall and post-stall flow behaviors
  • Partial effectiveness of the actuator noted even at 18° angle of attack

Cite This Study

Norimoto et al. (2025) studied this question.

synapsesocial.com/papers/69c4ccbbfdc3bde448918372https://doi.org/10.1299/jsmemecj.2025.s054-12
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