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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| Other Authors: | |
| Format: | Final Year Project (FYP) |
| Language: | English |
| Published: |
2014
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| Online Access: | http://hdl.handle.net/10356/61009 |
| _version_ | 1811695198285070336 |
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| author | Tan, Hao Chong |
| author2 | Jorg Uwe Schluter |
| author_facet | Jorg Uwe Schluter Tan, Hao Chong |
| author_sort | Tan, Hao Chong |
| collection | NTU |
| description | 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. |
| first_indexed | 2024-10-01T07:19:39Z |
| format | Final Year Project (FYP) |
| id | ntu-10356/61009 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T07:19:39Z |
| publishDate | 2014 |
| record_format | dspace |
| spelling | ntu-10356/610092023-03-04T18:40:41Z Design of a morphing airfoil Tan, Hao Chong Jorg Uwe Schluter School of Mechanical and Aerospace Engineering DRNTU::Engineering::Aeronautical engineering::Aerodynamics 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. Bachelor of Engineering (Aerospace Engineering) 2014-06-04T02:15:00Z 2014-06-04T02:15:00Z 2014 2014 Final Year Project (FYP) http://hdl.handle.net/10356/61009 en Nanyang Technological University 135 p. application/pdf |
| spellingShingle | DRNTU::Engineering::Aeronautical engineering::Aerodynamics Tan, Hao Chong Design of a morphing airfoil |
| title | Design of a morphing airfoil |
| title_full | Design of a morphing airfoil |
| title_fullStr | Design of a morphing airfoil |
| title_full_unstemmed | Design of a morphing airfoil |
| title_short | Design of a morphing airfoil |
| title_sort | design of a morphing airfoil |
| topic | DRNTU::Engineering::Aeronautical engineering::Aerodynamics |
| url | http://hdl.handle.net/10356/61009 |
| work_keys_str_mv | AT tanhaochong designofamorphingairfoil |