ABSTRACT

Wing thickness is an important parameter that affects aerodynamic characteristics of wind tunnel models. Although theoretical tools for designing of high performance aircraft were initially of limited value, simple methods were used to design that became accepted benefiting overall aircraft performances. This paper describes the effects of wing thickness on aerodynamic characteristics of constructed wind tunnel testing models. For this purpose we choose NACA 4315, NACA 4412 and NACA 1408. The maximum wing thickness of NACA 4315, NACA 4412 and NACA 1408 are 15cm, 12cm and 8cm respectively. In this experimental study a subsonic wind tunnel test has been performed with different attack angles and Reynolds numbers. The Reynolds numbers are 0.17×10⁵, 0.26×10⁵, 0.34×10⁵, 0.43×10⁵ and 0.52×10^5. The experimental result shows that the wing of having less thickness experienced lower drag than the wing of higher thickness i.e. the wing of NACA1408 experienced lower drag than the wing of NACA4412 and NACA4315.

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