Open AccessInvestigation into the Effects of Turbulent Air Flow on Stall of a NACA 2412 Airfoil Using Spalart-Allmaras Turbulence Model in STARCCM+
Author(s) -
Zhexin Wang,
Yuwen Su
Publication year - 2021
Publication title -
progresivna tehnìka, tehnologìâ ta ìnženerna osvìta
Language(s) - English
Resource type - Journals
ISSN - 2409-7160
DOI - 10.20535/2409-7160.2021.xxii.238887
Subject(s) - airfoil , stall (fluid mechanics) , angle of attack , turbulence , mechanics , naca airfoil , flow separation , relative wind , vortex , physics , aerospace engineering , geology , materials science , meteorology , engineering , aerodynamics , reynolds number
The simulation results of the air flow around NACA 2412 airfoil in STARCCM+ are submitted. The 9 groups of comparative experiments were simulated at 9 angles of attack: 0, 10, 13, 14, 15, 16, 18, 20, 30 degrees. By analyzing the air flow near the upper surface airfoil, the relationship between the generation condition of separation vortex and the angle of attack and the law of change of angle of attack and lift force were obtained. Finding the range of angle of attack for the stall, the angle of attack with maximum lift effectiveness was determined.