Rotor blade system for a turbine engine

A turbine engine comprising:

• a fan section;
• a compressor section;
• and
• a turbine section, wherein at least one of the fan section, the compressor section, or the turbine section includes a rotor blade system comprising:
• a rotor;
• and
• a plurality of blades coupled to the rotor, the plurality of blades arranged in an airfoil distribution pattern, the airfoil distribution pattern comprising one or more baseline blades and one or more intentionally mistuned blades,
• wherein the one or more intentionally mistuned blades have a span from a base of the one or more intentionally mistuned blades to a tip of the one or more intentionally mistuned blades and a chord defined from a leading edge of the one or more intentionally mistuned blades to a trailing edge of the one or more intentionally mistuned blades, and
• wherein the one or more intentionally mistuned blades includes a mistuning feature, the mistuning feature includes a notch formed on a surface of the one or more intentionally mistuned blades, the mistuning feature being located at a vicinity of the tip of the one or more intentionally mistuned blades to generate a vibration frequency difference between a vibration frequency of the one or more intentionally mistuned blades and a baseline natural vibration frequency of the one or more baseline blades.