PLAZMA AKTÜATÖRÜN NACA2415 AIRFOIL ETRAFINDA AKIŞ KONTROLÜNE ETKİLERİNİN ARAŞTIRILMASI

Abstract

Bu çalışmada, değişen Reynolds sayılarında ve hücüm açılarında plazma aktüatörlerin akış kontrolüne etkisi incelenmiştir. Plazma aktüatör NACA2415 airfoil üzerinde x/C=0.1 konumuna yerleştirilmiştir. Aktüatörün aktif akış kontrolüne etkisi Reynolds sayısının 8x103 ile 9x104 aralığında rüzgar tünelinde incelenmiştir. NACA2015 tipi uçak kanat profiline etki eden kaldırma kuvveti, kuvvet balans sistemi kullanılarak ölçülmüştür. Hız ölçümleri, iz bölgesine konumlandırılan kızgın tel probu ile ölçülmüş ve model etrafindaki akış duman tel yöntemi ile görselleştirilmiştir. Plazmanın aktif olduğu durumda, kaldırma katsayısında artış ve iz bölgesinde daralma gözlemlenmiştir. Düşük Reynolds sayılarında etkili aktif akış kontrolü ile akış ayrılması daha yüksek hücüm açılarına kaydırılmıştır. Akış ayrılması önlenmesi 18° hücum açısına kadar artırılmıştır ve 14° de gerçekleşen en yüksek kaldırma kuvveti plazma aktüatörün çalıştırılması ile iki katına çıkmıştır.

Keywords

• airfoil
• akış kontrolü
• kaldırma kuvveti
• plazma aktüatör

INVESTIGATING THE EFFECTS OF PLASMA ACTUATOR ON THE FLOW CONTROL AROUND NACA2415 AIRFOIL

Abstract

In this study, the effects of the plasma actuator on flow control at varied Reynolds numbers and attack angles are examined. Plasma actuator is placed on the NACA2415 airfoil at x/C = 0.1. The effect of the actuator to active flow control is examined at Reynolds number between 8x103 and 9x104 in the wind tunnel. The lift force which acted on the airfoil was measured by using a force balance system. The velocity measurements were done by the hot-wire probe, located at the wake region, and the flow around model was visualized by the smoke wire method. When the plasma was active, an increased lift force and a narrowed wake region are observed. The stall angle shifted to the higher attack angle by the effective active flow control at low Reynolds numbers. Prevent of the flow separation was enhanced up to 18° angle of attack and the maximum lift force occurred at the 14° angle of attack which is doubled when the plasma actuator is on.

Keywords

• airfoil
• flow control
• lift force
• plasma actuator

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