| Summary: | Approved for public release: Distribution is unlimited === Experimental results are presented which describe the development and
structure of flow downstream of one row and downstream of two staggered rows
of film-cooling holes with compound angle orientations. Results presented include
distributions of iso-energetic Stanton number ratios, and adiabatic film-cooling
effectiveness deduced from Stanton numbers using superposition. Also presented
are plots showing the streamwise development of injectant distributions and
streamwise development of mean velocity distributions. Spanwise averaged
values of the adiabatic film-cooling effectiveness are highest for blowing ratio
m=0.5 and decrease as blowing ratio increases for x/d less than 20. At farther
downstream positions, spanwise averaged effectiveness values increase with
blowing ratio, except for data obtained downstream of two rows of holes with a
blowing ratio of 3.0 and data obtained downstream of two rows of holes with a blowing ratio of 3.0 and data obtained downstream of one row of holes with a
blowing ratio of 4.0, where severe lift-off of injectant occurs. Spanwise averaged
iso-energetic Stanton number ratios range between 1.0 and 1.4 and show little
variation as x/d increases for each value of blowing ratio, however for each x/d,
values increase with increasing blowing ratio.
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