# 천음속영역에서 에어포일의 공력해석 자동화 및 해석코드 검증

• 김현 (한국항공대학교 대학원 항공우주 및 기계공학과) ;
• 정형석 (공군사관학교 항공우주공학과) ;
• 장조원 (한국항공대학교 항공운항학과) ;
• 최주호 (한국항공대학교 항공우주 및 기계공학과)
• Published : 2006.09.30

#### Abstract

Aerodynamic analysis of an airfoil in the transonic region was automated in order to enable parametric study by using the journal file of the commercial analysis code FLUENT, pre/post process Gambit and computational mathematics code MATLAB. The automated capability was illustrated via NACA 0012 and RAE 2822 airfoils. This analysis was carried out at Mach numbers ranged from 0.70 to 0.80, angles of attack; 1$^{\circ}$, 2$^{\circ}$ and 4$^{\circ}$, Reynolds numbers; 4.0${\times}$106, 6.5${\times}$106. The analysis results of a pressure coefficient were verified by comparing with the experimental data which were measured in terms of chord length because the pressure coefficient of an airfoil surface is a good estimator of flow characteristics. The results of two airfoils show that this analysis code is useful enough to be used in the design optimization of airfoil.