NACA0012 CFD - Computational Design Optimization - Adjoint

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Computational design of a NACA0012 airfoil for maximal lift/drag ratio.
AOA = 1.25 degrees
Mach = 0.8
Sensitivity derivatives were taken using a discrete adjoin approach and the mesh movement was applied with linear elastic smoothing to avoid grid line crossing.

Design variables were point locations on the upper surface and Hicks-Henne function parameters controlling the camber of the airfoil.

Category:

Science & Technology

Tags:

• CFD
• computational design
• NACA0012
• engineering
• aerodynamics