An experimental investigation of fluidic jet vectoring using counter-flow method had been carried out in this current work. The experimental investigation included a set of experiments to examine the various effects of geometric variables on the thrust vectoring angle. These included Coanda surface radius R/d = (0.58823, 1.17647, 1.75471), secondary gap height h/d = (0.02941, 0.05882), and secondary mass flow ratio range of (0 ≤ S / p ≤ 0. 07882). In addition, the test rig was built to display the ability of counter-flow method to vector the primary flow in pitch and yaw axes. Load cell readings were obtained using two components overhead balance. The results show proportional increase in vectoring angle value with the increase of the secondary suction rate. Three zones can be observed: a "dead zone" region at low mass flow ratios, followed by a control region where continuous primary jet control is achievable until a saturation region is reached. Small Coanda surface ratio resulted in an extended dead zone. The secondary gap height increase had an inverse effect on the thrust vectoring angle. A Smoke visualization was carried out to augment the experimental work and to demonstrate primary flow vectoring in pitch, and yaw axes. The investigation shows that the experimental gave a good agreement compared with previous studies on jet vectoring angle.