nomad-vagabond : NACA 2412 Backward-facing Step Analysis
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Aerodynamic Coefficients of NACA 2412 Airfoil With Backward-Facing Step
Over the last decade, aircraft morphing technology has drawn a lot of attention in the aerospace community, because it is likely to improve the aerodynamic performance and the versatility of aircraft at different flight regimes. With the fast paced advancements in this field, a parallel stream of research is studying different materials and designs to develop reliable morphing skins. A promising candidate for a viable morphing skin is the sliding skin, where two or more rigid surfaces remain in contact and slide against each other during morphing. The overlapping between each two panels create a backward-facing step on the airfoil surface which has a critical effect on the aerodynamics of the wing [1].
This repository contains results of a numerical study of the effect of employing a backward-facing step on the suction side of a NACA- 2412 airfoil at a Reynolds number of 5.9 × 106 [1]. Particularly, relations of lift and drag coefficients to the angle of attack are reconstructed using smoothing splines.
References
[1] Fadi Mishriky, Paul Walsh; Effect of the Backward-Facing Step Location on the Aerodynamics of a Morphing Wing, Aerospace 3, 25; 2016; doi:10.3390/aerospace3030025
Aerodynamic Coefficients of NACA 2412 Airfoil With Backward-Facing Step
Over the last decade, aircraft morphing technology has drawn a lot of attention in the aerospace community, because it is likely to improve the aerodynamic performance and the versatility of aircraft at different flight regimes. With the fast paced advancements in this field, a parallel stream of research is studying different materials and designs to develop reliable morphing skins. A promising candidate for a viable morphing skin is the sliding skin, where two or more rigid surfaces remain in contact and slide against each other during morphing. The overlapping between each two panels create a backward-facing step on the airfoil surface which has a critical effect on the aerodynamics of the wing [1].
This repository contains results of a numerical study of the effect of employing a backward-facing step on the suction side of a NACA- 2412 airfoil at a Reynolds number of 5.9 × 106 [1]. Particularly, relations of lift and drag coefficients to the angle of attack are reconstructed using smoothing splines.
References
[1] Fadi Mishriky, Paul Walsh; Effect of the Backward-Facing Step Location on the Aerodynamics of a Morphing Wing, Aerospace 3, 25; 2016; doi:10.3390/aerospace3030025
