Active Flow Control over a NACA23012 Airfoil using Hybrid Jet
نویسندگان
چکیده
A time-dependent numerical simulation is performed to examine the flow separation control with action of a hybrid jet (the combination synthetic and continuous jets) over NACA23012 airfoil. The unsteady Reynolds-averaged Navier–Stokes (URANS) Spalart-Allmaras (SA) turbulence model simulate field around airfoil analyse effect jet. combined placed at point on upper surface which located 12% chord length from leading edge for given configuration. Flow simulations are chord-based Reynolds number 2.19 × 106 oscillating frequency 0.159 blowing ratio 3.0. contribution in evident by control. Variation velocity studied, improved aerodynamic characteristics maximum improvement lift drag observed 11.19 22.14 an angle attack 22 degree. stall also shows enhancement 18 degree 20
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ژورنال
عنوان ژورنال: Defence Science Journal
سال: 2021
ISSN: ['0011-748X', '0976-464X']
DOI: https://doi.org/10.14429/dsj.71.16468