Salınım hareketinin sapma açısı altındaki bir delta kanada etkileri

Öz

Bu çalışmada, süpürme açısı Λ=70º olan narin (slender) delta kanadın girdaplı akış yapısındaki değişimi, sapma açısı β=0º, 4º ve 8º karşısındaki değişimi, üç farklı ortalama hücum açısında αm =25º, 30º ve 35º boya deneyi incelemesi amaçlanmıştır. Boya ile nitel görselleştirme deneyleri, Re=2x104 gerçekleştirilmiştir. Kanat modeli istenilen açıda sabitlenerek ve elde edilen deney sonuçlar dikkate alınarak, α0=±0.5º ve ±1º genliğinde ve Te =0.5s, 1s ve 2s periyotlarında kanata sürekli salınım hareketi verilerek girdap çökmesinin belirli ölçüde kontrolü sağlanmaya çalışılmıştır. Ancak, uçağın manevra sırasında maruz kaldığı düşük frekanslı bozulmaların etkileri incelenmiştir. Kelvin-Helmholtz girdaplarının narin delta kanadın daimî salınım hareketi verilen durumunda statik vaka sonuçlarından daha belirgin olduğu gözlenmektedir. Narin delta kanatlarının sıfır sapma açısı, β salınımı hareketi anında; girdap çökme konumu statik durumdan daha geniş bir aralıkta ileri ve geri hareket etmektedir.

Anahtar Kelimeler

• Boya ile Görselleştirme
• Delta kanat
• Hücum açısı
• Salınım hareketi
• Sapma açısı

The influence of perturbation motion over a slender delta wing under sideslip angle

Abstract

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 Λ=70º under the alteration of three different sideslip angles of β=0º, 4º, and 8º at three different main angles of attack of αm=25º, 30º and 35º experimentally. Dye visualization experiments were conducted at a Reynolds number of Re=2x104 to analyze qualitatively. The perturbation motion which has amplitudes of α0=±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, β.

Keywords

• Angle of attack
• Delta wing
• Dye visualization
• Perturbation motion
• Sideslip angle

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