Düşük Süpürme Açısına Sahip Delta Kanat Modeli Üzerinde Oluşan Aerodinamik Karakteristiklerin İncelenmesi

Özet

Aerodinamik, delta kanatlar ve mikro hava araçları (MAVs) da dahil olmak üzere basitleştirilmiş modeller ile temsil edilebilen insansız savaş hava araçlarında (UCAVs), son yıllarda önemli bir yer almıştır. Delta kanatlar üzerinde oluşan girdap dinamiği ve bu girdapsal akışın kanadın performansına etkileri kilit bir rol haline gelmiştir. Bu çalışmanın amacı düşük süpürme açısına sahip delta kanat (? = 510) üzerinde oluşan akışın fiziğini ve aerodinamik performansını boya görüntüleme ve kuvvet ölçüm sistemi kullanarak anlamaktır. Farklı hücum açılarında, 50

Abstract

The aerodynamics of unmanned combat air vehicles (UCAVs), which can be represented by simplified planforms, including delta wings, and micro air vehicles (MAVs) have taken important place in recent years. Vortex dynamics over delta wing and the effects on delta wing performance have become an important key role. The aim of this investigation is to underlying flow physics and to understand aerodynamic performance over non-slender diamond wing having low sweep angle (Λ = 510) by using dye flow visualization and force measuring systems (Submersible S Beam Junior Load Cell and two torque sensors). The flow visualization of vortex flow structure, the formation of the vortex breakdown, lift and drag force (FL and FD) as aerodynamic forces, over the wing in terms of the different angle of attacks, α, with in the range of 50≤ α ≤ 300were studied under static condition. Force measurements and dye flow visualization are carried out in a water tunnel to explain the dynamic characteristics of the non-slender wing model. Experimental investigation includes the time-averaged velocity components for dye-visualization, the coefficients of lift and drag force (CL and CD), for aerodynamic performance with different angle of attacks. It was concluded that vortex breakdown occurred far from the trailing-edge of the wing at low angle of attack. The results show that aerodynamic lift and drag coefficient, and pitching moment are strongly affected by the vortex interactions as the angle of attack changes. CL, and CD, are also affected by the vortex breakdown and stall condition for different angle of attacks