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Dergiler / Bitlis Eren Üniversitesi Fen Bilimleri Dergisi / 2026 / Volume: 15 Issue: 2

Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing

Ahmet Ertuğrul Bay(GAZIANTEP UNIVERSITY, INSTITUTE OF SCIENCE, ELECTRICAL AND ELECTRONIC ENGINEERING (DR))0000-0002-5740-7165
Tolgay Kara(GAZIANTEP UNIVERSITY, FACULTY OF ENGINEERING)0000-0003-3991-8524
Sayfa
—
Yayın Tarihi
2026-06-30
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⚡ TL;DR(1 Cümlede Hızlı Çıkarım)

In addition to the detailed observation of vortex structures and the comparison of aerodynamic forces, the results revealed that the non-slender wing exhibited a smooth stall characteristic, contrasting with the sharper stall typically observed in standard fixed-chord NACA 2412 wings.

📌 3 Maddede Bu Makale

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Amaç & Hipotez:The vortex structures formed on non-slender delta wings are highly related to the sweep angle and leading-edge geometry.
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Temel Bulgular & Veri:This study investigates the aerodynamic performance parameters of a NACA 2412-based non-slender delta wing.
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Sonuç & Katkı:In addition to the detailed observation of vortex structures and the comparison of aerodynamic forces, the results revealed that the non-slender wing exhibited a smooth stall characteristic, contrasting with the sharper stall typically observed in standard fixed-chord NACA 2412 wings.
🔬Tür:Research Article
📍Kapsam:Genişletilmiş Akademik Örneklem
⚙️Değişkenler:NACA 2412 delta wing · Aerodynamic performance · Surface oil visualization

Abstract

The vortex structures formed on non-slender delta wings are highly related to the sweep angle and leading-edge geometry. This study investigates the aerodynamic performance parameters of a NACA 2412-based non-slender delta wing. Aerodynamic forces, including lift and drag coefficients, were measured to determine the maximum lift-to-drag ratio. Additionally, flow structures on the suction surface and in the wake region were examined using titanium-dioxide-based surface oil visualization and the tuft-grid technique. Results indicate a maximum lift coefficient of 0.9256 at a 21° angle of attack, and a maximum lift-to-drag ratio of 5.2553 at 9°. Surface oil visualization demonstrated the movement of vortex breakdown toward the apex and highlighted unswept flow areas over the wing. Tuft-grid analysis, applied at different chord distances (1C, 2C, and 3C) from the trailing edge, revealed that the vortex cores expand and shift downward as they move downstream. In addition to the detailed observation of vortex structures and the comparison of aerodynamic forces, the results revealed that the non-slender wing exhibited a smooth stall characteristic, contrasting with the sharper stall typically observed in standard fixed-chord NACA 2412 wings.

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Bu Makaleye Atıf Yap

Bay, A. E., Kara, T. (2026). Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi, Volume: 15 Issue: 2. https://doi.org/10.17798/bitlisfen.1847172

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