Uçağın Kanat Hücum Kenarında Buzdan Arındırma Performansını Etkileyen Parameterelerin Optimizasyonu

Year 2022, Issue: 34, 19 - 27, 31.03.2022

Hayati Kadir Pazarlıoğlu Ahmet Ümit Tepe Kamil Arslan

https://doi.org/10.31590/ejosat.1062495

Abstract

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.

Keywords

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.

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