Blade outer seal for a gas turbine engine

A gas turbine engine, comprising:

• an engine case;
• a rotor stage having a plurality of blades;
• and
• a blade outer air seal disposed between the engine case and the blades, which blade outer air seal comprises a body that extends between a forward edge and an aft edge, and includes:
• an outer radial surface;
• an inner radial surface that has at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section;
• and
• a plurality of cooling air apertures, where each cooling air aperture extends between the outer radial surface and the riser, and where each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface.