CORE
🇺🇦
make metadata, not war
Services
Services overview
Explore all CORE services
Access to raw data
API
Dataset
FastSync
Content discovery
Recommender
Discovery
OAI identifiers
OAI Resolver
Managing content
Dashboard
Bespoke contracts
Consultancy services
Support us
Support us
Membership
Sponsorship
Community governance
Advisory Board
Board of supporters
Research network
About
About us
Our mission
Team
Blog
FAQs
Contact us
Sensitivity analysis and uncertainty quantification for the ffowcs williams-hawkings equation
Authors
23rd AIAA/CEAS Aeroacoustics Conference
S. Abraham
+3 more
Francesco Contino
G. Ghorbaniasl
N. Ricks
Publication date
1 January 2017
Publisher
Abstract
The acoustic propagation stage of a computational aeroacoustic analysis has been in- vestigated for possible sources of uncertainty and sensitivity. The acoustic propagation is realized through an acoustic prediction module that is fundamentally based on the Ffowcs Williams-Hawkings equation. Non-intrusive polynomial chaos expansion methods are used, along with a direct sensitivity analysis based on Sobol indices. Three analytical test cases are chosen in order to isolate the acoustic propagation stage from the noise source identification stage. In an analysis of a theoretical helicopter blade, it is identified that the mean flow Mach number and blade tip Mach number are significant contributors to noise uncertainty. As the advancing blade tip Mach number approaches the transonic and supersonic flow regimes, these uncertainties are amplified. The source of the uncertainty is mainly attributed to the blade tip Mach number at low mean flow Mach numbers, however as the mean flow Mach number increases, the contribution of the mean flow Mach number to the uncertainty significantly increases. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved
Similar works
Full text
Available Versions
DIAL UCLouvain
See this paper in CORE
Go to the repository landing page
Download from data provider
oai:dial.uclouvain.be:boreal:2...
Last time updated on 15/02/2020