ملخص البحث :
The main idea of this paper is to give a profound investigation of the aerodynamic properties of a wing for
Cessna 172S. The numerical analysis of total drag is developed by using various methods from different references, the
2D and 3D lift curve parameters of the wing Cessna 172S are generated according to the analysis method depending on
empirical equations. The first stage of modelling Cessna 172S is evaluated according to the airfoil of Cessna NACA
2412, whereas the second stage of modelling is estimated by using wing planform properties. The maximum lift
coefficient, lift curve slope, zero angle of attack, lift at zero angle of attack, and stall angle of attack are calculated by
using different empirical equations.
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سنة النشر : -24
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تصنيف البحث : scopus
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