Abstract: An aircraft propeller blade comprising an inner section which extends from the propeller hub toward the blade tip, a middle section adjacent to said inner section, and an outer section which extends from adjacent to said middle section to the blade tip; where the largest camber in the inner section decreases linearly over the blade length from adjacent to the propeller hub toward the blade tip, and the greatest camber height location shifts linearly over the blade length toward the blade tip; the largest camber in the middle section increases linearly over the blade length toward the blade tip, and the greatest camber height location shifts approximately linearly from adjacent to the inner section toward the blade tip; and the camber in the outer section decreases elliptically over the blade length toward the blade tip, and the greatest camber height location remains constant from adjacent to the middle section to the blade tip.