What is it about?
The aerodynamic parameter this paper engages with is the Lift to Drag ratio curve, which is perhaps the most concise value corresponding to aerodynamic performance of a flying object. This paper investigates the effect of trailing edge serrations on the lift to drag ratio of a 3D wing. A design parametrization approach was followed during the research where a wide array of dimensions of triangular serrations were tested in CFD simulations and later, the best performing wings were manufactured and tested in Wind-Tunnel to verify the simulation model. A second stream of the research added curvature to the triangular serrations (the side-lines of the triangle were replaced with 2nd-order splines) and its effects were compared with the simple serrations.
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Why is it important?
The aero-acoustic advantage of serrations have been widely investigated, however, their aerodynamic effects have been largely untouched and there is little in the way of design optimization or development of correlations with respect to sizing of serrations. Especially novel is the addition of curvature and the consequent study of its effects on serrated wings. There is no other established literature on the idea and the kind of advantages in terms of reduced drag induction when compared to straight-edged triangular serrations has wide ranging implications in Wind-Turbine technology and drones that fly in the sub-sonic range.
Perspectives
The idea behind this research was to study how Owls with their serrated wings are not just quiet but do not seem to face any flight disadvantage when it comes to their peers (Falcons). The investigation later led us to try various trailing edge geometries and a wide array of literature review. A special consideration was given to development of a high-fidelity CFD setup and that is the backbone of our conclusions.
SAIF UL MALOOK
Read the Original
This page is a summary of: Effect of trailing edge serration on the lift and drag characteristics of NACA0012 airfoil wing, June 2017, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2017-4470.
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