The effect of a cross-stream jet flow control applied to a two-dimensional generic NACA 65(2)-415 inlet guide vane (IGV) is studied for chord-based Reynolds number ranging from fifty thousand up to one million. The commercial software program ANSYS Fluent is used for the simulation of the IGV with Reynolds Averaged Navier-Stokes(RANS) models. Various RANS and wall models are compared including the standard k − ω, SST k − ω, standard k − ε, realizable k − ε, and transition shear stress transport (SST) turbulence model. The results are compared to X-Foil, a solver based on a coupled potential flow model with an integral boundary layer model, and previously conducted experiments. The SST model is the only model that successfully captures the transition from a laminar to a turbulent boundary layer. All other models can only model turbulent boundary layers. The SST model closely matches X-Foil results and experimental results for Reynolds numbers greater than one hundred thousand. For a Reynolds number of fifty thousand X-Foil underpredicts lift. Two cross-stream jets, modeled as point sources, are placed at two different locations, one is tangent to the surface on the suction side at 60% chord and the other is perpendicular to the chord line on the pressure side at 87% chord. The suction side jet generally delays separation and reattaches the flow. The trailing edge jet applied to the pressure side functions as a gurney flap mechanism that creates a pressure lift increase. A combined pressure and suction synthetic jets improve lift and reduce drag for the IGV. Increasing the Reynolds number promotes early separation, followed by reattachment. A synthetic jet actuated parallel to the flow on the suction side of the airfoil will postpone flow separation. At higher Reynolds numbers the strength of the synthetic jet diminishes and has less than two percent difference. Therefore, the strength of the synthetic jet is increased to accommodate for higher Reynolds numbers.