Bulk how pulsations in the form of sinusoidal variations of velocity and static pressure at injectant Strouhal numbers from 0.1-10.1 are investigated as they affect film cooling from a single row of simple angle holes. Similar flow variations are produced by potential flow interactions and passing shock waves near turbine surfaces in gas turbine engines. Time-averaged temperature distributions, phase-averaged temperature distributions, adiabatic film cooling effectiveness values, and iso-energetic Stanton numbers show that important alterations to film cooling protection occur at different ranges of frequencies and coolant Strouhal numbers as non-dimensional injection hole length is changed.