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

Year 2024, EARLY VIEW, 1 - 1

Ahmet Fatih Kaya

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

Cited By: 1

Abstract

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.

Keywords

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

Abstract

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°.

Keywords

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

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