Abstract
The present paper intends to improve the aerodynamic performance of a NACA4415 airfoil using low-profile vortex generators. Numerical flow analysis yielded the values of the lift and drag coefficients for impacts ranging from incidence 0&deg; to 24&deg;. The steady Reynolds averaged Navier Stokes equations have been solved with the ANSYS CFX 2019 R2 calculation tool utilizing the shear stress transport turbulence model at a Reynolds number Re &#61; 2.13 &times; 10<sup>5</sup>. The approach of tetra-mixed meshing was employed. The impact of several parameters (height, span-wise distance, installation angle &beta;, skew angle &phi;) have been investigated. Experimental data has been used to validate the results. According to the numerical outcomes, the skewed angle vortex generators (&Phi; &#61; 20&deg;) placed upstream of the separation zone with a short spanwise distance are beneficial for delaying the stall angle from &alpha; &#61; 20&deg; (clean airfoil) to &alpha; &#61; 24&deg; and enhance the lift coefficient by 39&#37;. However, the overall optimal lift-to-drag ratio was achieved when &phi; &#61; 0&deg;.
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