The influence of perturbation motion over a slender delta wing under sideslip angle
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Tarih
2021
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
In this study, the main objective is to reveal the change of the vortical flow characteristics on a slender delta wing with a sweep angle of ?=70º under the alteration of three different sideslip angles of ?=0º, 4º, and 8º at three different main angles of attack of ?m=25º, 30º and 35º experimentally. Dye visualization experiments were conducted at a Reynolds number of Re=2x104to analyze qualitatively. The perturbation motion which has amplitudes of ?0=±0.5º and ±1º was applied continuously under the periods of time of Te=0.5s, 1s, and 2s. However, the effects of the low frequency perturbations to which the aircraft is exposed during the maneuver were examined. It is observed that Kelvin-Helmholtz in the case of the perturbed motion vortices is more prominent than static case results of the slender delta wing. The vortex breakdown location on the perturbed delta wing has been changed in a wider range than the static case of the delta wing at zero sideslip angle, ?.
Açıklama
Anahtar Kelimeler
Fizik, Uygulamalı, Mühendislik, Makine, Mühendislik, Hava ve Uzay
Kaynak
Niğde Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi
WoS Q Değeri
Scopus Q Değeri
Cilt
10
Sayı
1
