Bir Düz Flaplı Simetrik Kanat Profilinin Aerodinamik Karakteristiğine Kiriş Yapısı Etkisinin İncelenmesi

Yıl 2024, Cilt: 27 Sayı: 3, 967 - 974, 25.07.2024

Ahmet Fatih Kaya

https://doi.org/10.2339/politeknik.1159822

Cited By: 1

Öz

Bu çalışmada düz flapa sahip bir NACA 0018 kanat profilin aerodinamik performansına kiriş etkisi iki boyutlu olarak Hesaplamalı Akışkanlar Dinamiği yöntemi ile incelenmiştir. Ağ yapısından bağımsızlığa ulaşıldıktan sonra deneysel çalışma Spalart-Allmaras türbülans modeli ile doğrulanmıştır. M1 (düz flapsız ve kiriş yapısız kanat), M2 (kiriş yapısına sahip kanat), M3 ( düz flaplı kanat) ve M4 (düz flaplı ve kiriş yapısına sahip kanat) olmak üzere 4 farklı kanat yapısı modellenmiştir. Kanatların aerodinamik performansları kaldırma katsayısının sürükleme katsayısına oranı (C_L/C_D) bulunarak hesaplanmıştır. Çalışmanın sonucunda düz flap yapısı, kaldırma katsayısı (C_L) ve sürükleme katsayısını (C_D) önemli ölçüde arttırmıştır. Kiriş yapısı düz flapa sahip olmayan kanadın aerodinamik performansını atak açısı 12°’den büyük olduğunda arttırmışken, flap yapısına sahip olan kanadın aerodinamik performansını neredeyse bütün atak açılarında yükseltmiştir. Aynı zamanda kiriş yapısı, bütün atak açıkarında düz flapa sahip olan kanatta gözlemlenen C_D değerlerini azaltmış ve atak açısı 2°’den büyük olduğu durumda C_L değerlerini arttırmıştır.

Anahtar Kelimeler

Sayısal analiz, kanat profili, düz flap, kiriş yapısı, sürükleme katsayısı, kaldırma katsayısı

Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

Öz

In this paper, two-dimensional computational fluid dynamics analyses were conducted to examine the rib effect on the performance of the NACA 0018 plain flapped airfoil. A mesh independence study was carried out and the Spalart-Allmaras turbulence model was selected for validation. Four various airfoil models were designed: M1 (airfoil without plain flap and rib structure), M2 (airfoil with rib structure), M3 (airfoil with a plain flap) and M4 (airfoil with a rib structure and plain flap). The performance of designed airfoils was calculated in terms of lift-to-drag (C_L/C_D) ratio. As a result, the plain flap significantly increased the lift coefficient (C_L) and drag coefficient (C_D). While the rib structure enhanced the aerodynamic performance of the non-flapped airfoil when the attack angle was greater than 12°, it increased the performance of the plain flapped airfoil at almost all attack angles. Furthermore, it was seen that the rib structure decreased C_D values of plain flapped airfoil at all attack angles and increased C_L values of plain flapped airfoil when the attack angle was greater than 2°.

Anahtar Kelimeler

Numerical analysis, airfoil, plain flap, rib structure, drag coefficient, lift coefficient

Kaynakça

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