نوع مقاله : مقاله پژوهشی
نویسندگان
1 دانشجوی دکتری مهندسی مکانیک، مرکز تحقیقات انرژی‌های تجدیدپذیر، واحد دماوند، دانشگاه آزاد اسلامی، دماوند، ایران
2 عضو هیات علمی / پژوهشگاه هوافضا-وزارت علوم
3 استادیار، مرکز تحقیقات انرژی‌های تجدیدپذیر، واحد دماوند ، دانشگاه آزاد اسلامی ، دماوند ، ایران
چکیده
کلیدواژه‌ها
عنوان مقاله [English]
نویسندگان [English]
In this study, the effect of blowing angle on coefficients of aerodynamic of NACA0012 airfoil at Re=4×106 has been investigated. The changes of lift and drag coefficients were studied by using the blowing near the leading edge of the airfoil for angles of attack of 12, 14, 16, 18 and 20 degrees. Due to the application of blowing through circular holes, a three-dimensional solution was used for the purpose of analysis and study, which will be computationally expensive. The analysis carried out in this case was performed with the assumption of incompressible and steady flow around a three-dimensional wing section in Fluent software. The results showed that the blowing has a negligible effect on the lift and drag coefficients at angles of attack less than 14 degrees. It is for this reason that only the effects of the blowing at high angles of attack are considered. The greatest increase in the lift coefficient and the greatest decrease in the drag coefficient occurs at the angle of attack of 16 degrees, which is the stall angle. Also, the angle of the blowing jet relative to the airfoil and the effect of this parameter on the aerodynamic coefficients and flow separation were studied computationally. The results showed that as the jet angle increases, the aerodynamic performance decreases. It was also observed that the jet with an angle of 90 degree has the worst performance, so that it has a lower aerodynamic performance than the one without the jet.
کلیدواژه‌ها [English]
)