Publikationsdatum:
2019-06-27
Beschreibung:
The development of separation in corners of thrust augmentor wings having Coanda jets was investigated using hot film surface sensors and pressure transducers. Separation on the test augmentor began at a corner very close to the augmentor exit and then rapidly proceeded upstream. Measurements of the pressure fields in the corner region indicated that a modified form of the Stratford criterion could be used to predict the onset of separation. Testing was conducted over a range of nozzle pressure ratios, aspect ratios, diffuser angles, and designs of the boundary layer and Coanda nozzles.
Schlagwort(e):
AERODYNAMICS
Materialart:
NADC-76153-30
,
NASA. Ames Res. Center Workshop on Thrust Augmenting Ejectors; p 273-293
Format:
application/pdf
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