International Journal of Aerospace Sciences
pISSN: 21698872 eISSN: 21698899
2016; 4(1): 18
doi:10.5923/j.aerospace.20160401.01
S. MartínezAranda^{1}, A. L. GarcíaGonzález^{2}, L. Parras^{2}, J. F. VelázquezNavarro^{2}, C. del Pino^{2}
^{1}Faculdade de Engenharia, Universidade do Porto, Porto, Portugal
^{2}Universidad de Málaga, E.T.S. Ingeniería Industrial, Málaga, Spain
Correspondence to: A. L. GarcíaGonzález, Universidad de Málaga, E.T.S. Ingeniería Industrial, Málaga, Spain.
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Copyright © 2016 Scientific & Academic Publishing. All Rights Reserved.
This work is licensed under the Creative Commons Attribution International License (CC BY).
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This experimental work deals with the influence of the angle of attack (AoA) and the chord based Reynolds number (Re_{c}) on the lift and drag coefficients for a lowaspectratio NACA0012 airfoil. In addition, we provide novel general correlations for the minimum drag coefficient together with the ratio between the maximum lift and the minimum drag coefficient for different Reynolds numbers and several aspect ratios, after comparing our experimental data with other research works. This information is very useful for future validation of numerical simulations. Furthermore, we observe that the change in the aerodynamic characteristics are linked to the variations in the linear slope of the lift coefficient as function of AoA for any aspect ratio, thus finding a critical Reynolds number Re_{c}=10^{5} at which the slope saturates its value and the maximum of the polar curve changes its upward trend.
Keywords: Low Reynolds Number, Wing Aerodynamics, Aspect ratio, Wingtip Vortex
Cite this paper: S. MartínezAranda, A. L. GarcíaGonzález, L. Parras, J. F. VelázquezNavarro, C. del Pino, Comparison of the Aerodynamic Characteristics of the NACA0012 Airfoil at LowtoModerate Reynolds Numbers for any Aspect Ratio, International Journal of Aerospace Sciences, Vol. 4 No. 1, 2016, pp. 18. doi: 10.5923/j.aerospace.20160401.01.
Figure 1. Schematics of experimental setup with the wing model mounted 

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Figure 5. C_{L} vs αfor Re_{c} = 3.33·10^{4} and Rec = 6.67·10^{4} with AoA values lower than the stall angle (AR = 2), together with Laitone’s data [22] (AR = 6, I = 0.02%) 
Figure 8. LiftDrag ratio C_{L}/C_{D} vs angle of attack α. The inset shows C_{D} vs C_{L} for all Reynolds numbers tested 