Airfoil Optimization Design by Panel Methods for Small Size Aerial Vehicle at Low Reynolds Number

DOI

10.2991/mems.2012.87How to use a DOI?

Keywords

low Reynolds number; airfoil optimization; panel method; lifting coefficient

Abstract

Airfoil optimization design has been carried out by panel methods for small size aerial vehicle at low Reynolds number. The optimization airfoil formulas were expressed by the NACA4 digital airfoil analytical expressions with a few optimization variables that made the optimizing computation quick. A system of n+1 dimensional linear equations have been derived from vortex panel and source panel methods to compute the vortex and source strengths on the airfoil surface and aerodynamic coefficients in airfoil optimization process. The airfoil was optimized under the condition of taking the maximum lifting coefficient of taking off or landing without stall for optimization goal by Matlab optimization toolbox. The aerodynamic analysis results of optimized airfoil by XFOIL indicate that the lifting coefficients all have some extent increase relative to drag coefficients in the range of 0-12 degrees of angle of attack respectively.

Copyright

© 2012, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - LIU Wu-fa
AU  - LI Su-yan
AU  - GONG Zhen-bang
AU  - JIANG Zhen
PY  - 2012/12
DA  - 2012/12
TI  - Airfoil Optimization Design by Panel Methods for Small Size Aerial Vehicle at Low Reynolds Number
BT  - Proceedings of the 1st International Conference on Mechanical Engineering and Material Science (MEMS 2012)
PB  - Atlantis Press
SP  - 327
EP  - 330
SN  - 1951-6851
UR  - https://doi.org/10.2991/mems.2012.87
DO  - 10.2991/mems.2012.87
ID  - Wu-fa2012/12
ER  -