Design of a morphing airfoil
This report studies the aerodynamic effects of a small single shape-morphing hump on a 2D NACA 4412 airfoil surface under a free stream of 0.7 Mach number and various cruising angle of attacks ranging from 0 degree to 4 degrees. The results are collected using Reynolds Averaged Navier Stokes Simulat...
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| Format: | Final Year Project (FYP) |
| Language: | English |
| Published: |
2014
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| Online Access: | http://hdl.handle.net/10356/61009 |
| Summary: | This report studies the aerodynamic effects of a small single shape-morphing hump on a 2D NACA 4412 airfoil surface under a free stream of 0.7 Mach number and various cruising angle of attacks ranging from 0 degree to 4 degrees. The results are collected using Reynolds Averaged Navier Stokes Simulations (RANS) solver from well known Computational Fluid Dynamics (CFD) software known as ANSYS Fluent.
Methodology of the study has been discussed, including mesh creation and solver settings. Mesh independence test and validation with experimental wind tunnel results have also been conducted and covered in the report.
The final results of aerodynamic effects by various hump configurations have been collected and analyzed. Possible implementation and application of small single hump on wing surface have also been discussed. |
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