Datasheet-Experimental and Computational Strategies for Improving the Aerodynamic Performance with SETE

Paper Title: Experimental and Computational Strategies for Improving The Aerodynamic Performance with SETE

Paper Abstract: An open-loop wind tunnel experiment and Computational Fluid Dynamics simulations are carried out on several Static Extended Trailing Edge (SETE) attached to the  NACA0012 airfoil wing model to investigate the effect of a SETE on the aerodynamic characteristics at low Reynolds. A thin extended trailing edge of length 20% of the chord and 15° deflection appears to generate 74.24% more lift concerning the baseline model. SETE enables a smooth, gradual stall, resulting in more time for stall recovery. A high benefit margin makes SETE an ideal option to achieve more cruise flight efficiency.

*This repository contains:

Datasheet 

Datasheet Contents:

Sheet 1: Wind Tunnel Experiment Data (Paper section IV.A.3)

Sheet 2: CFD Simulation Data (Paper section IV.B.3)

Sheet 3: Baseline Model (Paper section IV.A.1-2)

Sheet 4: Calculation of Lift Increment (Paper section IV.C)

Sheet 5: Calculation of Benefit Margin (Paper section IV.D)

Sheet 6: Coefficient of Pressure sample (Paper section IV.B.3)

CAD geometries in .STEP format

Ansys Workbench files (Upon request)

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