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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Bibliographic Details
Main Author: Tan, Hao Chong
Other Authors: Jorg Uwe Schluter
Format: Final Year Project
Language:English
Published: 2014
Subjects:
Online Access:http://hdl.handle.net/10356/61009
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Institution: Nanyang Technological University
Language: English
Description
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.