NACA-2412

This work was originally intended to perform adjoint optimization technique to optimize the shape of the aerofoil for maximum lift and minimum drag. But unfortunately my simple work station couldn't handle the load and the simulation time was painfully long. Hence, it became a simple steady simulation.

Result

Flow Domain
Surface mesh
Aerofoil cross section (pointy part of the trailing edge is removed for the surface wrapper to work properly)
Velocity
Pressure (negative pressure over the aerofoil indicates lift)
Cp at 9% wingspan
Cp at 52% wingspan
Cp at 73% wingspan
Element Count 1.99E+06
Velocity 288.12 m/s
AoA 0 degree
Reference area for drag 0.0139 m2
Reference area for lift 0.1116 m2
Drag Coefficient, Cd 0.1259
Lift Coefficient, Cl 0.1772
Email

rahmanf247@gmail.com
1512014@name.buet.ac.bd

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Mirpur Circle -1, Dhaka, Bangladesh