This paper presents simulations of 3D co-flow jet (CFJ) active flow control airfoil with an embedded micro-compressor actuator. The injection and suction ducts geometries, slot locations and micro-compressor interface boundary conditions are determined based on the design of 2D CFJ airfoil and micro-compressor actuator. The simulations are performed at Mach number 0.15 to simulate the cruise condition of a general aviation aircraft. The airfoil used in this work is CFJ-NACA-6421. The simulations employ 3D RANS solver with Spalart-Allmaras (S-A) turbulence model, 3th order WENO scheme for the inviscid fluxes, and 2nd order central differencing for the viscous terms. The aerodynamic performance, energy expenditure, and 3D flow field are compared between the CFJ airfoils with different jet momentum coefficient (Cµ) and maximum swirl angle at the injection duct inlet (βmax). An CFJ airfoil with ideal ducts and a baseline airfoil are also studied as reference for comparison. The parametric study results show that the lift coefficient (CL) and power coefficient (Pc) linearly increase with the rise of Cµ, while the drag coefficient (CD) and productivity efficiency ((CL 2/CD)c) linearly decreases with the rise of Cµ. A large βmax leads to a more favorable mass flow rate distribution at the injection slot, which suppresses the flow separation at the injection slot edges and improves the aerodynamic performance. However, a too large βmax leads to flow separation inside the injection duct and increase the pumping energy loss. The results of this work will guide the future high efficiency CFJ airfoil design optimization and the design for wind tunnel testing with embedded micro-compressors.