This paper is Part II of a parametric study on CFJ airfoils. In the first part of the paper, the CFJ airfoil suction surface shape is modified to reduce or overcome the nose-down moment. In the second part of the paper, the injection and suction sizes and Cμ are varied to increase the CFJ airfoil thrust generation. For both parts, the resulting effects on the lift, drag, moment and energy consumption is analyzed. The two dimensional flow is simulated using steady and unsteady Reynolds Average Navier-Stokes (RANS). A 5th order WENO scheme for the inviscid flux, a 4th order central differencing model for the viscous terms and the one equation Spalart- Allmaras model for the turbulence are used to resolve the flow. The Mach number is 0.15 and Reynolds number is 6.4 × 106. The nose-down moment of the CFJ airfoils was successfully reduced with the use of reflex camber while negative drag was achieved with a thinner airfoil, and a reduced injection size. Increasing Cμ further reduces the drag, but at the cost of a much higher energy consumption and reduced corrected aerodynamic efficiency. The minimum drag achieved is CD = -0.033 and the highest moment achieved is CM = 0.031.