Publication Date:
2019-08-16
Description:
A full-scale wind-tunnel test was conducted of two boundary-layer-control applications to a 44-foot diameter helicopter rotor. Blowing from a nozzle near the leading edge of the blades delayed retreating blade stall. Results also indicated that delay of retreating blade stall could be obtained by cyclic blowing with a lower flow rate than that required for continuous blowing. It was found that blowing applied through a nozzle at mid-chord had no effect on retreating blade stall.
Keywords:
Fluid Mechanics and Heat Transfer
Type:
NASA-TN-D-335
,
A-380
Format:
application/pdf
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