This work focuses on the design and multi-parametric analysis of a designed propeller for a Pentacopter unmanned aerial vehicle (UAV). The basic and secondary design inputs, along with performance data like propeller diameter, pitch angle, chord length, and lift coefficient, are established using a standard analytical method. Approximately ten distinct airfoils, specifically NACA 2412, NACA 4109, NACA 4312, NACA 4409, NACA 4415, NACA 5317, NACA 6409, NACA 6412, NACA 23024, and NACA 25012, are evaluated over 13 Reynolds Numbers with the angle of attacks (AOA) of 20, varying from -5 to 15 degrees, for the purpose of detailed propeller design. The lift and drag coefficient values for ten distinct airfoils, utilizing a Reynolds number of 13 and 20 angles of attack, are obtained from the XFOIL software. Three sophisticated airfoils are selected from a pool of ten based on their high Lift-to-Drag (L/D) ratio performance. The selected airfoils with a high L/D ratio are NACA 6409, NACA 4109