The effect of three-dimensional, longitudinal contouring of jet engine nozzle afterbodies is investigated experimentally in a water tunnel facility. Both laminar and turbulent Reynolds numbers are tested for three different afterbody configurations. Results indicate that forced mixer lobe technology can be applied to nozzle afterbodies and decrease drag coefficient by as much as 70 %. Improved exhaust mixing is also possible through such contouring. Exhaust gas attenuation benefits of 125 % have been recorded.
Lobed nozzle afterbody research
Erforschung des ungleichmaessigen Duesenhinterteils
AIAA-Papers ; Jul ; 1-9
1987
9 Seiten, 14 Bilder, 12 Quellen
Aufsatz (Konferenz)
Englisch
Lobed nozzle afterbody research
AIAA | 1987
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