The exploration of flat plates as lift-generating devices has been limited in existing studies. Given the increasing significance of low Reynolds number applications, especially in the field of Micro Aerial Vehicles operating within the Reynolds number range of 104–105, there is a growing need for comprehensive investigations. Notably, conventional airfoil wings demonstrate an inferior performance at these low Reynolds numbers, making the use of flat-plate wings a potentially superior alternative. In this particular investigation, we delved into the phenomenon of vortex shedding in the wake of a flat plate at a low angle of attack. The experimental procedures were carried out in the controlled environment of a low-speed subsonic wind tunnel, maintaining a Reynolds number of 5 × 104. To capture and analyze the velocity patterns in the wake of the flat plate, a hot wire anemometer was employed. The systematic measurements were strategically executed at specific locations, both across the flow direction in the wake and above the suction side of the flat plate. This scrutiny revealed a consistent and repetitive nature in the variations of velocity within the wake. Notably, the frequency at which vortices detached from the trailing edge of the flat plate demonstrated a tendency to increase with the angle of attack.