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

Ahmet Ertuğrul Bay; Tolgay Kara

doi:10.17798/bitlisfen.1847172

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

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.

Keywords

References

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Details

Primary Language

English

Subjects

Aerodynamics (Excl. Hypersonic Aerodynamics), Aircraft Performance and Flight Control Systems

Journal Section

Research Article

Authors

Ahmet Ertuğrul Bay ^*
0000-0002-5740-7165
Türkiye

Tolgay Kara
0000-0003-3991-8524
Türkiye

Publication Date

June 30, 2026

Submission Date

December 22, 2025

Acceptance Date

April 24, 2026

Published in Issue

Year 2026 Volume: 15 Number: 2

DOI

https://doi.org/10.17798/bitlisfen.1847172

IZ

https://izlik.org/JA78GC73SD

Cite

RIS / Bibtex

APA

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, 15(2), 928-937. https://doi.org/10.17798/bitlisfen.1847172

AMA

1.Bay AE, Kara T. Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi. 2026;15(2):928-937. doi:10.17798/bitlisfen.1847172

Chicago

Bay, Ahmet Ertuğrul, and Tolgay Kara. 2026. “Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing”. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi 15 (2): 928-37. https://doi.org/10.17798/bitlisfen.1847172.

EndNote

Bay AE, Kara T (June 1, 2026) Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi 15 2 928–937.

IEEE

[1]A. E. Bay and T. Kara, “Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing”, Bitlis Eren Üniversitesi Fen Bilimleri Dergisi, vol. 15, no. 2, pp. 928–937, June 2026, doi: 10.17798/bitlisfen.1847172.

ISNAD

Bay, Ahmet Ertuğrul - Kara, Tolgay. “Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing”. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi 15/2 (June 1, 2026): 928-937. https://doi.org/10.17798/bitlisfen.1847172.

JAMA

1.Bay AE, Kara T. Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi. 2026;15:928–937.

MLA

Bay, Ahmet Ertuğrul, and Tolgay Kara. “Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing”. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi, vol. 15, no. 2, June 2026, pp. 928-37, doi:10.17798/bitlisfen.1847172.

Vancouver

1.Ahmet Ertuğrul Bay, Tolgay Kara. Aerodynamic Performance and Vortex Structure Investigations for A NACA2412 Based Non-Slender Delta Wing. Bitlis Eren Üniversitesi Fen Bilimleri Dergisi. 2026 Jun. 1;15(2):928-37. doi:10.17798/bitlisfen.1847172