Numerical Investigation of Different Airfoils at Low Reynolds Number in terms of Aerodynamic Performance of Sailplanes by using XFLR5

Year 2018, , 47 - 65, 18.06.2018

İbrahim Halil Güzelbey , Yüksel Eraslan , Mehmet Hanifi Doğru

https://doi.org/10.31466/kfbd.423932

Cited By: 8

Abstract

Wing design has a critical
importance for sailplanes as well as for all the aircrafts in terms of
aerodynamic performance. One of the important design phases of an
aerodynamically efficient sailplane wing is selection of the appropriate
airfoil. Airfoil selection of a wing design firstly requires performing
aerodynamic performance analyses of different airfoils to compare according to
determined requirements. In this study, numerical investigation of nine
different airfoils was performed with the aim of comparison in terms of
aerodynamic performance of sailplanes by using the general public licensed
computer program XFLR5. Firstly, the airfoils which will be compared were
selected from Eppler, Goettingen, NACA and Wortmann airfoil families. For the
comparison of the airfoils, the two-dimensional analysis validation of the
program was done with experimental data, and the airfoils were analyzed in two
dimensions under the same validated analysis conditions. The analyses were
performed at 2x10⁵ Reynolds number and angle of attacks from -5 to
20 degrees. According to obtained results from the analyses, the airfoils were
compared in terms of determined criteria which are thickness, maximum lift
coefficient and its angle of attack, maximum drag to lift ratio, drag
coefficient at maximum lift condition, pitching moment at zero lift condition and
power factor.

Keywords

Sailplane, Wing design, Airfoil, XFLR5, Aerodynamic performance

Numerical Investigation of Different Airfoils at Low Reynolds Number in terms of Aerodynamic Performance of Sailplanes by using XFLR5

Abstract

Kanat tasarımı, tüm hava
araçları için olduğu gibi, planörler için de aerodinamik performans açısından
kritik öneme sahiptir. Aerodinamik olarak verimli bir planör kanadı tasarımının
en önemli aşamalarından biri de uygun kanat kesit geometrisi (kanat profili)
seçimidir. Bir kanat tasarımının kanat kesit geometrisi seçimi, öncelikle
belirlenen gerekliliklere dayanarak karşılaştırmak üzere, farklı kanat kesit
geometrilerinin aerodinamik performans analizlerini gerektirir. Bu çalışmada,
dokuz farklı kanat kesit geometrisi planör aerodinamik performansı açısından
karşılaştırmak üzere genel kamu lisanslı XFLR5 programı kullanılarak nümerik
olarak incelenmiştir. Öncelikle karşılaştırılacak geometriler Eppler,
Goettingen, NACA ve Wortmann kanat kesit geometrisi ailelerinden seçilmiştir.
Karşılaştırma için programın deneysel verilerle iki boyutlu doğrulaması
yapılmış ve seçilen kanat kesit geometrileri aynı koşullar altında analiz
edilmiştir. Analizler 2x10⁵ Reynolds
sayısında ve -5 ile 20 derece arasındaki hücum açılarında gerçekleştirilmiştir.
Analizlerden elde edilen sonuçlara göre kanat kesit geometrileri belirlenen
gereklilikler olan kalınlık, maksimum kaldırma katsayısı ve hücum açısı,
maksimum kaldırma durumundaki sürüklenme katsayısı, maksimum süzülme oranı,
sıfır kaldırma durumundaki yunuslama momenti ve güç faktörüne göre
karşılaştırılmıştır.

Keywords

Planör, Kanat tasarımı, Kanat kesit geometrisi, XFLR5, Aerodinamik performans

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