Abstract
A 2D mixer-ejector nozzle device with the acoustically lined wall has been developed for jet noise reduction to achieve the noise level equivalent to ICAO Annex 16 Chapter 3 regulation with minimum thrust losses. In order to investigate flight effects on noise reduction and thrust losses, flight model test were made at the CEPRA19 anechoic wind tunnel in France. Upstream flow conditions of mixer such as velocity profile and temperature profile were simulated as close as the real engine. In this report, some of above experimental test results are presented including noise reduction characteristics by the porous ceramic matrix composites acoustic liner inserted to the ejector shroud and the trend of thrust losses of the mixer ejector nozzle in forward flight. NOMENCLATURE CEPRA19 anechoic wind tunnel CMC acoustic liner EPNL effective perceived noise level [EPNdB]
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