Uçağın Kanat Hücum Kenarında Buzdan Arındırma Performansını Etkileyen Parameterelerin Optimizasyonu

Öz

Bu çalışmada, uçuş esnasında tehlikeli durumlardan biri olan uçak kanat hücum kenarı üzerinde buz birikimi sayısal olarak araştırılmıştır. Hedef yüzey Tw=263.15 K derecede sabit tutulurken, giriş sıcaklığı Tin=473.15 K olarak m ̇=0.004 kg/s. ile sisteme iletilmiştir. Araştırma NACA 0015 kullanarak sayısal çalışmanın sabit piccolo tüp ölçüleri, jet açısı ve jetler ve jet-hedef yüzey mesafeleri için doğrulama çalışması ile başlamıştır. İkinci ve üçüncü aşamada farklı jet açıları (30°≤≤150°) altında X (4≤H/d≤8) ve Y (-1.25≤L/d≤1.25) yönünde değişen piccolo tüp pozisyonlarının buzdan arındırma performansını incelemektir. Dördüncü aşama buzdan arındırma sisteminin performansını maksimum taşınım ısı transfer ve minimum basınç azalımı durumu ile arttırmak için optimum H/d, L/d ve oranlarını belirlemektir. Optimizasyon çalışması Yüzey Cevap Metodolojisi kullanılarak yapılmıştır. Sonuç olarak, teklif edilen tasarımda en yüksek buzdan arındırma performansı ° L/d=0.0 ve H/d=4.0 kullanılarak başarılırken, optimizasyon çalışmaları maksimum ısı transfer oranı ve minimum basınç düşüşü değerini başarmak için  L/d ve H/d değerlerinin sırasıyla 55.45°, 0.0 ve 4.0 olması gerektiğimi göstermiştir.

Anahtar Kelimeler

• Optimizasyon
• Buzdan Arındırma
• NACA 0015
• Yüzey Cevap Metodolojisi
• HAD

Optimization of Parameters Affecting Anti-Icing Performance on Wing Leading Edge of Aircraft

Abstract

In this article, one of the hazardous trouble in-flight situations called ice accumulation on wing leading edge of aircraft has been numerically investigated. While the target surface is kept constant temperature at Tw=263.15 K, the inlet temperature is taken constant at Tin=473.15 K and it enters to the system with m ̇=0.004 kg/s. The investigation starts with validation of numerical study utilizing airfoil type of NACA 0015 using constant piccolo tube dimensions, jet angle, distance among jets and distance between jet-to-target positions. The second and third stages are to analyze the anti-icing performance of changing positions of piccolo tube on X (4≤H/d≤8) and Y (-1.25≤L/d≤1.25) directions under different jet angles (30°≤≤150°). The fourth stage is to determine the optimum H/d, L/d, and ratios to increase anti-icing performance with maximum convective heat transfer and minimum pressure drop condition. The optimization study has been done using Response Surface Methodology (RSM). Finally, while the best anti-icing performance proposed design is achieved using° L/d=0.0, and H/d=4.0, the optimization results show that the L/d, and H/d values should be 55.45°, 0.0, and 4.0, respectively to achieve maximum heat transfer rate with minimum pressure drop value.

Keywords

• Optimization
• Anti-Icing
• NACA 0015
• Response Surface Methodology (RSM)
• CFD.

Kaynakça

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