The aerodynamic design of an aircraft propeller requires a proper choice of design conditions among which the engine characteristics (power, revolutions) and the design flight speed are essential. Especially fixed propellers are considerably affected by the design point because their best operation corresponds to a single flight speed only. The paper deals with the design of aerodynamic characteristics of a propeller aimed at achieving maximum efficiency at a chosen design regime. Frequently the design point is selected at the flight speed providing the maximum rate of climb. The presented propeller design is specified for the Z-226 airplane with the WALTER M-137 engine.