Control of vortex breakdown over the non-slender lambda wing
Aerospace Science and Technology, cilt.179, 2026 (SCI-Expanded, Scopus)
- Yayın Türü: Makale / Tam Makale
- Cilt numarası: 179
- Basım Tarihi: 2026
- Doi Numarası: 10.1016/j.ast.2026.113372
- Dergi Adı: Aerospace Science and Technology
- Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Compendex, INSPEC, zbMATH, Academic Search Ultimate (EBSCO), Engineering Source (EBSCO)
- Anahtar Kelimeler: Lambda wing, Piv, Pulsation, Turbulent statistics, Vortex control
- Çukurova Üniversitesi Adresli: Evet
Özet
A non-slender lambda wing (NSLW) with a sweep angle of Λ=40° was subjected to continuous and periodic oscillatory motion to investigate the formation, evolution, stability, and disintegration characteristics of a leading-edge vortex (LEV). Experiments were conducted at Reynolds numbers Rec =1 × 104 based on the wing cord and Reh = 61,285 based on the open-channel hydraulic diameter, with a uniform velocity of 59.5 mm/s . The non-slender lambda wing was subjected to a small-amplitude harmonic perturbation defined as α(t)= α¯ +Δα sin (ωe t), with the excitation period varied between 0.5 s and 1 s, with an oscillation amplitude of Δα= 1° It was determined that applying excitations to the wing near the characteristic frequency, fe , of LEV bursting significantly altered the development of the shear layer adjacent to the wing surface and the spatial position of the LEV breakdown, leading to significant restructuring of the instantaneous and time-averaged flow field.