Localized riblets for a flowpath surface

A turbine engine compressor airfoil comprising:

• a body having a root coupled to a hub or casing of a turbine engine, the body extending in a radial direction from the root to a tip and in an axial direction from a leading edge to a trailing edge, the body defining a pressure side, and a suction side opposite the pressure side;
• a ribbed section on the suction side of the body, the ribbed section comprises a plurality of riblets each extending at least 90% of a chord length from the leading edge to the trailing edge at a span-wise location from the root to the tip,
• wherein the airfoil includes a first section and a second section, wherein the first section includes a first density of discrete localized riblets on the suction side and the second section includes a second density of discrete localized riblets on the suction side, wherein the first density is greater than the second density, wherein the first density includes the ribbed section and is 1%-20% of a span from the root to the tip, and wherein the second density is 80%-99% of the span.