Numerical Study of Plasma Actuator Placement for Flow Separation Control on a NACA 6412 Airfoil

دیوازی, آرش; نوفرستی, عرفان; حاجی‌پور, مجید

doi:10.22034/jtae.2026.1417

Numerical Study of Plasma Actuator Placement for Flow Separation Control on a NACA 6412 Airfoil

نوع مقاله : علمی پژوهشی

نویسندگان

آرش دیوازی ¹

عرفان نوفرستی ²

مجید حاجی‌پور ³

¹ دانشجوی کارشناسی ارشد، دانشکدگان علوم و فناوری‌های میان‌رشته‌ای، دانشگاه تهران، تهران، ایران

² دانشکده مهندسی مکانیک، دانشگاه فردریکو دوم ناپل

³ دانشکدگان علوم و فناوری‌های میان‌رشته‌ای، دانشگاه تهران، تهران، ایران

10.22034/jtae.2026.1417

چکیده

We numerically assess how chordwise placement of a single dielectric barrier discharge (DBD) plasma actuator affects separation control on a cambered NACA 6412 airfoil at α = 12° for U∞ = 1 and 10 m/s (Re ≈ 6.85×10^4 and 6.85×10^5, respectively). Steady RANS (SST k-ω) is coupled with a Shyy-type body-force model to represent the actuator. In the baseline, separation forms on the suction side with onset near x/c ≈ 0.60 at 1 m/s and x/c ≈ 0.70 at 10 m/s. Four plasma actuator locations are evaluated: x/c = 0.03 (LEL), 0.10 (LER), 0.40 (TEL), and 0.65 (TER). Simulation results indicated that placement strongly governs authority by determining where momentum is added to the boundary layer. A leading-edge actuator at x/c ≈ 0.03 consistently yields the best outcome, delaying or removing separation, strengthening the suction peak, and promoting smooth pressure recovery, especially at 10 m/s. A downstream actuator near x/c ≈ 0.65 is the next most effective, targeting the vicinity of natural separation. LER (x/c ≈ 0.10) is the least effective, especially at 10 m/s, where residual trailing-edge separation remains. For placements aft of the maximum thickness, very strong actuation (plasma jet ≫ free-stream) can induce a laminar separation bubble and increase drag despite lift gains. These findings offer practical guidance for selecting actuator position and strength on cambered airfoils at moderate incidence.

کلیدواژه‌ها

Flow Control

DBD Plasma Actuator

Separation

Control

Momentum Injection

NACA 6412

موضوعات

آئرودینامیک/مکانیک سیالات/آئروآکوستیک/...

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