ENITEP

Experimental and Numerical Investigation of Turbulent Boundary Layer Effects on Noise Propagation in High Speed Conditions

Coordinatore	AIRCRAFT RESEARCH ASSOCIATION LIMITED    more  Organization address address: Manton Lane city: BEDFORD postcode: MK41 7PF contact info Titolo: Mr. Nome: Andrea Cognome: Hill Email: send email Telefono: +44 1234 324694
Nazionalità Coordinatore	United Kingdom [UK]
Totale costo	750˙000 €
EC contributo	512˙450 €
Programma	FP7-JTI Specific Programme "Cooperation": Joint Technology Initiatives
Code Call	SP1-JTI-CS-2012-01
Funding Scheme	JTI-CS
Anno di inizio	2012
Periodo (anno-mese-giorno)	2012-12-01   -   2016-05-31

 Partecipanti

#	participant	country	role	EC contrib. [€]
1	AIRCRAFT RESEARCH ASSOCIATION LIMITED  Organization address address: Manton Lane city: BEDFORD postcode: MK41 7PF contact info Titolo: Mr. Nome: Andrea Cognome: Hill Email: send email Telefono: +44 1234 324694	UK (BEDFORD)	coordinator	427˙350.00
2	MSC SOFTWARE BELGIUM  Organization address address: RUE EMILE FRANCQUI 1 AXIS PARK city: MONT SAINT GUIBERT postcode: 1435 contact info Titolo: Prof. Nome: Jean-Louis Cognome: Migeot Email: send email Telefono: 3210451226	BE (MONT SAINT GUIBERT)	participant	85˙100.00

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 Obiettivo del progetto (Objective)

'A requirement has been produced to perform a combination of experimental wind tunnel tests and numerical simulations to study the phenomena of acoustic refraction through the aerodynamic boundary layer over a fuselage. The aim of the research will be to acquire and utilise experimental acoustic data to validate and develop numerical simulation methods in order to better understand the complex phenomena of noise transmission from Contra-rotating Open Rotor engines (CROR) into the aircraft cabin at cruise conditions. The research will utilise a significant number of existing test components and acoustic instrumentation to maximise the quantity of unique experimental data obtained. The tests will be performed in the ARA 2.74m x 2.44m Transonic Wind Tunnel using an acoustic liner insert to create a near anechoic environment in the working section. An existing fuselage model will be utilised, incorporating extensive steady and unsteady pressure sensor installations and a large array of microphones. An existing tonal noise source will also be utilised. Aircraft Research Association Ltd (ARA) proposes to apply its extensive experience and expertise in wind tunnel testing and model design and manufacture to lead this programme of work. ARA will liaise with the CfP leader during the design and manufacture of the test hardware and subsequent wind tunnel tests, developing and exploiting current state of the art techniques including traversing mechanisms for the hot-wire probes and high-speed acoustic data recording. The numerical acoustic simulations will be performed by Free Field Technologies (FFT) using CAA (Computational Aero-Acoustics) codes, which will be assessed and developed using the experimental acoustic data from the wind tunnel tests.'