38 of the rotor blade 30 and the shroud assembly 34 the rotor blade 30 includes an airfoil 40 having a leading edge 42 and a trailing edge 44 a chord 46 of the airfoil 40 extends between the leading edge 42 and the trailing edge 44 a span 48 of the airfoil 40 extends between a root 50 and the tip region 38 of the rotor blade 30 the root 50 of the rotor blade 30 is adjacent to a platform 52 that connects the rotor blade 30 to a rotating drum or disk not shown in a known manner the airfoil 40 of the rotor blade 30 also includes a suction surface 54 and an opposite pressure surface 56 the suction surface 54 is a generally convex surface and the pressure surface 56 is a generally concave surface the suction surface 54 and the pressure surface 56 are designed conventionally to pressurize the airflow as airflow f is communicated from an upstream direction u to a downstream direction dn the airflow f flows in an axial direction x that is parallel to the longitudinal centerline axis a of the gas turbine engine a the rotor blade 30 rotates in a rotational direction circumferential y about the engine centerline axis a the span 48 of the airfoil 40 is positioned along a radial axis z.