The aeroacoustics of an innovative regional turboprop aircraft is experimentally investigated on a 6.5 scaled model. The measurement campaign was performed at the RUAG Large Subsonic Wind Tunnel in Emmen. The model was mounted on a ceiling strut in the 7-by-5 meters test section, not acoustically treated. The aeroacoustic noise generated by the aircraft model was evaluated analyzing the pressure fluctuations acquired through a phased array of 144 microphones installed on a flat-plate on the test section floor. Pressure fluctuations were acquired in different configurations the most important ones being: the baseline solution (no innovative device applied) with engine on and the model equipped with lined Flap. For the engine on configuration, take-off and approach settings were tested, whereas only the landing configurations was investigated for the baseline lined flap comparison. The main parameters varied during the tests were: the propeller thrust, the propeller revolutions per minute, the speed of the air-flow, the incidence angle of the aircraft and the position of the microphone array. Data were processed and then analyzed in the frequency domain and using a conventional beamforming algorithm to retrieve the sound source map over the areas of interest. Source maps were deconvolved with a CLEAN-SC routine and single source contributions determined through integration of auto-powers.

Di Marco, A., Camussi, R., Burghignoli, L., Centracchio, F., Averardo, M., Di Giulio, M., et al. (2018). Aeroacoustic wind tunnel testing of a 1:6.5 model scale innovative regional turboprop. In 2018 AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA [10.2514/6.2018-3601].

Aeroacoustic wind tunnel testing of a 1:6.5 model scale innovative regional turboprop

Di Marco, Alessandro
;
Camussi, Roberto;Burghignoli, Lorenzo;Centracchio, Francesco;
2018-01-01

Abstract

The aeroacoustics of an innovative regional turboprop aircraft is experimentally investigated on a 6.5 scaled model. The measurement campaign was performed at the RUAG Large Subsonic Wind Tunnel in Emmen. The model was mounted on a ceiling strut in the 7-by-5 meters test section, not acoustically treated. The aeroacoustic noise generated by the aircraft model was evaluated analyzing the pressure fluctuations acquired through a phased array of 144 microphones installed on a flat-plate on the test section floor. Pressure fluctuations were acquired in different configurations the most important ones being: the baseline solution (no innovative device applied) with engine on and the model equipped with lined Flap. For the engine on configuration, take-off and approach settings were tested, whereas only the landing configurations was investigated for the baseline lined flap comparison. The main parameters varied during the tests were: the propeller thrust, the propeller revolutions per minute, the speed of the air-flow, the incidence angle of the aircraft and the position of the microphone array. Data were processed and then analyzed in the frequency domain and using a conventional beamforming algorithm to retrieve the sound source map over the areas of interest. Source maps were deconvolved with a CLEAN-SC routine and single source contributions determined through integration of auto-powers.
9781624105609
Di Marco, A., Camussi, R., Burghignoli, L., Centracchio, F., Averardo, M., Di Giulio, M., et al. (2018). Aeroacoustic wind tunnel testing of a 1:6.5 model scale innovative regional turboprop. In 2018 AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA [10.2514/6.2018-3601].
File in questo prodotto:
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11590/347478
Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 0
  • ???jsp.display-item.citation.isi??? ND
social impact