Transonic shock wave boundary layer interaction control using a combination of swirling flow and vortex generators

This research presents the results of numerical analysis of a co-rotating array of Mini Swirling Air Jet Vortex Generators (Mi-SAJVGs) installed on the supercritical P-18-415 airfoil profile wing model at an angle of attack $\alpha$ = 4$^\circ$. The active flow control system is aimed to be operated when the flight is in cruise mode. Simulations were conducted under conditions representative of steady state cruise mode flight, with a freestream Mach number of $\mathrm{M}_\infty$ = 0.75 at which point shock wave separation occurs in the boundary layer. Ansys Fluent software is utilized to solve 3D compressible Reynolds Averaged Navier–Stokes (RANS) equations, employing the two-equations $k$–$\varepsilon$-realizable turbulence model. The study identifies the optimal design configuration based on pressure coefficient $(C_p)$ and the lift-to-drag ratio $(K=C_l/C_d)$.