NUMERICAL INVESTIGATION OF FLOW CHARACTERISTICS OF A NON-SLENDER LAMBDA WING UNMANNED AERIAL VEHICLE

Yıl 2022, Cilt: 9 Sayı: 18, 481 - 490, 31.12.2022

Haci Sogukpinar , Serkan Cag

https://doi.org/10.54365/adyumbd.1085034

Öz

In this paper, the low-speed aerodynamic performance of lambda wing with a chord length of c=210 mm and sweep angle of Λ =51°, thickness 3 mm, and beveled leading edges on the windward side with an angle of 58° is investigated numerically. Reynolds Average Navier Stokes (RANS) theorem equations with Spalart-Allmaras turbulence model were solved up to an angle of attack 45° for incompressible flow around the wing surface and, are compared to experiment to corralete simulation precision of computational fluid dynamic approaches. Detail about the aerodynamic performance of lambda wing including development and formation of the leading-edge vortex (LEV), the interaction of flow with the surface, flow separations, and stall are studied, presented, and discussed. LEV was started at 5°, vortex breakdown was observed at halfway along the leading edge at the angle of 20°, finally, by the time angle is 30°, bursting vortex gives a way to stall stage.

Anahtar Kelimeler

delta wing, lambda wing, LEV, CFD

Lambda Kanatlı İnsansız Hava Aracı İçin Sayısal Modelleme

Öz

Bu Çalışmada, kiriş uzunluğu c=210 mm, süpürme açısı Λ=51°, kalınlığı 3 mm ve rüzgar yönüne 58° açı ile eğimli hücum kenarına sahip lambda kanadının düşük hızlı aerodinamik performansı nümerik olarak incelenmiştir. Spalart-Allmaras türbülans modeli ile Reynolds Ortalama Navier Stokes (RANS) teorem denklemleri, kanat yüzeyi etrafındaki sıkıştırılamaz akış için 45°'lik bir hücum açısına kadar çözülmüş ve hesaplamalı akışkanlar dinamiği yaklaşımlarının simülasyon etkinliğini doğrulamak için deneysel verilerle karşılaştırılmıştır. Ön uç girdabının (LEV) gelişimi ve oluşumu, akışın yüzey ile etkileşimi, akış ayrımları ve stol dahil olmak üzere lambda kanadının aerodinamik performansı hakkında ayrıntılar incelenmiş ve tartışılmıştır. LEV oluşumu 5°'lik hücum açısında oluşmaya başlamış, 20°'lik eğimde hücum kenarı boyunca yarı yolda girdap kırılması gözlemlenmiş, son olarak hücum açısı 30° olduğunda, stol durumuna geçmiştir.

Anahtar Kelimeler

LEV, CFD, delta wing, lambda wing

Kaynakça

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