Effiziente Simulation von Aeroschallquellen. Roland Ewert Technische Akustik Institut für Aerodynamik und Strömungstechnik DLR Braunschweig
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1 DLR.de Folie 1 > Vortrag > Ewert werkstattgespräch_ewert.pptx > Effiziente Simulation von Aeroschallquellen Roland Ewert Technische Akustik Institut für Aerodynamik und Strömungstechnik DLR Braunschweig
2 DLR.de Folie 2 > Vortrag > Ewert werkstattgespräch_ewert.pptx > Sources of exterior/interior (interaction) noise at aircraft Re-Number of order 10mio! slat wing tip flap side edge landing gear wheel bay (cavities) Jet-Flap Interaction Jet Noise
3 Chart 3 Computational Aeroacoustic (CAA) Simulation Physical problems to be treated in aeroacoustics Sound generation broadband Sound generation broadband / tonal (1) Vortex shedding (2) Parker modes Sound generated by flows Aeroacoustics Sound propagation through flows (1) Sound-flow interactions (2) Fluid-acoustic feedback mechanisms (e.g. Cavity Noise)
4 Sound propagation CAA Codes PIANO and DISCO - PIANO code of DLR based on structured multi-block (SMB) meshes + finite differences - Dispersion Relation Preserving (DRP) scheme (Tam & Webb 1993) Volume discretization, moving medium 30P30N, PIANO SMB mesh (2-D) McDonnell Douglas (now Boeing) 30P30N profile - Discontinuous Galerkin methods for CAA (Bauer et al. 2011) - Simplified mesh generation based on unstructured meshes with high-order methods 30P30N, unstructured mesh (2-D, triangles) Disco (DGM) M. Bauer et al., 2011
5 CAA Code PIANO Sound propagation in flow Linearized Euler Equations (LEE) Acoustic Perturbation Equations (APE*) Linearized Navier-Stokes (LNS) Non-linear Euler Equations in perturbation form Non-linear Navier-Stokes in perturbation form (NLPE) prime : fluctuations over given flow Volume discretization, moving medium Sources to force sound LEE 0 : Mean-flow from steady RANS *JCP 188, 2003
6 CAA Code PIANO Sound propagation in flow Modellierung Propeller als rotierende Quellen (Input: RANS) Volume discretization, moving medium vorticity of 3 rotating point forces NWB test propeller induced leading edge sound flap sound sound field of 3 rotating point forces sound field of 3 rotating point forces + plate interaction Dierke, Delfs, Lenffers, Buchholz,Almoneit (Bürgernahes Flugzeug) CAA PIANO
7 Boundary Element Method - Memory 6 elements per wave length Number of triangle elements N, Surface A λ 2 A N 6 λ 2 A340: 341 Hz, 4000 Hz, 2 A 2250m 4 N N Matrix Elements: Single precision storage: Bytes, approx TB Memory Also working memory needed Tianhe-2 (1 of TOP500) has about 1024 TB Memory... 15
8 Fast Multipole Method Iterative solution of BEM equation Acceleration of matrix-vector product from O(N^2) to O(N log(n)) Splitting of every row of product into near and far field terms Calculation of far field interactions by a series expansion Far field contributions are collected and distributed over an Octree covering the geometry Example: Full scale aircraft (surface 582 m^2) 2,170,000 Triangles Wavelength 0.1 m (3410 Hz) 48 GB total memory (4 nodes) 150s for one iteration step on 32 cores (Opteron 2.7 GHz) 200 iteration steps (conjugate residual method)
9 Source: urans Sound: FMM BEM
10 Chart 10 Computational Aeroacoustic (CAA) Simulation Physical problems to be treated in aeroacoustics Sound generation broadband Sound generation broadband / tonal (1) Vortex shedding (2) Parker modes Sound generated by flows Aeroacoustics Sound propagation through flows (1) Sound-flow interactions (2) Fluid-acoustic feedback mechanisms (e.g. Cavity Noise)
11 Chart 11 Aeroacoustic Sound Sources From CFD RANS TAU RSM LES AIA Aachen Example: LuFo FREQUENZ
12 DLR.de Folie 12 > Vortrag > Ewert werkstattgespräch_ewert.pptx > /19 Vorhersage von Aeroschallquellen Turbulence related noise prediction Increasing computational complexity and time Increasing modeling assumptions Semi-empirical models Stochastic sound sources Scale resolving simulation BPM (NAFNoise) Hybrid RANS/CAA DNS/ LES Approach pursued by AS-TEA
13 DLR.de Chart 13 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Vorhersage von Aeroschallquellen RANS basiert: First-Principle + Prise Empirie
14 DLR.de Chart 14 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Sound generation from stochastic turbulence CAA Simulation of High-Lift Noise CAA validation DGM CAA solver DISCO SMB CAA solver PIANO DNW LLF experiment EU OPENAIR, M. Pott-Pollenske, M. Herr
15 DLR.de Chart 15 Vorticity from RANS derived vorticity correlation tensor Garski & Bernard:
16 DLR.de Chart 16 FRPM reconstructed vorticity correlations
17 Chart 17 Breitbandlärmvorhersage für turbulente Quellen Airframe Noise 2.5-D / 3-D 2-D Jet Noise Combustion Noise Haystacking / Spectral Broadening Surface excitation
18 Grenzschichtinduzierte Druckfluktuationen auf Rumpfoberfläche CFD-CAA (TAU/FRPM/PIANO) Simulation A320 ATRA vs. Flugversuch Herausforderungen: Einfluss Druckgradient Einfluss Machzahl Lufo-SIMKAB Hu, Appel, Herr
19 Prediction of jet flap interference (JFI) noise FRPM jet noise model to cover non axis-symmetric problems and installation effects AIAA , AIAA (FRPM literature: AIAA , AIAA ) full 3D FRPM jet noise model Development of relaxation source terms for forced eddy simulation AIAA to capture additional JFI noise sources Tam & Auriault source JFI noise maximum Eddy relaxation source Ewert, Neifeld
20 AIRBUS DEUTSCHLAND GmbH. Alle Rechte vorbehalten. Vertrauliches und geschütztes Dokument. FRPM sources combined with Fast Multipole Solver AP1320 COMPANOS Geschwindigkeitsrandbedingung für FM-BEM Code aus FRPM Fernfeldspektrum einer Simulation eines 2,5D-Flügelsegments zur Validierung Induced fluctuating velocities on FRPM domain Boundary condition for FM-BEM: Result: Farfield spectrum underneath slat FM-BEM sound propagation code Seite 20
21 DLR.de Chart 21 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Deterministic noise source model / Tones / Feed Back Tones (flow-acoustic feedback) not resolved AoA=18 Re=1.3e6 c=0.3m Ma=0.15 Broadband part of spectrum resolved F15 modified Acoustic Perturbation Equations (APE) Vortex Sound Sources CFD / RANS 2+1-D Synthetic Turbulence
22 DLR.de Chart 22 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Teilskalenauflösende Simulation The non-linear terms of the Navier-Stokes equations in perturbation form are the sources of the LEE (no source left ) Navier-Stokes, perturbation form?... Linearized Euler Equations (LEE)... Non-linear Sound Sources CFD / RANS 3+1-D Synthetic Turbulence
23 Unsteadiness (Spectral Content) fully prescribed (current situation) Physical Quality of Solution DLR.de Chart 23 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Teilskalenauflösende Simulation RANS URANS DES LES DNS combined physical quality unsteadiness prescribed part resolved part control parameter, grid dependent Computational Effort CAA with RANS based deterministic source model
24 DLR.de Chart 24 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Relaxation Source Term Test CAA Simulation of High-Lift Noise (AIAA ) DNW LLF experiment EU OPENAIR, M. Pott-Pollenske, M. Herr
25 DLR.de Folie 25 > Vortrag > Autor Dokumentname > Datum Danke für Ihre Aufmerksamkeit!
26 DLR.de Airfoil Trailing-Edge Noise Christof Rautmann AIAA Atlanta /19 Results NACA0012 (BANCII) CAA 1/3 octave band SPL spectra NACA0012; Ma=0.165; α=0, 4, 6 α=0 α=4 α=6 good agreement with experimental data AoA influence on spectra reproduced
27 DLR.de Folie 27 > Vortrag > Ewert werkstattgespräch_ewert.pptx > Sources of exterior noise at aircraft Re-Number of order 10mio! slat wing tip flap side edge landing gear wheel bay (cavities) Jet-Flap Interaction Jet Noise
28 DLR.de Chart 28 > AIAA 2014 > Ewert Presentation_AIAA_ewert.pptx > Teilskalenauflösende Simulation Goal: Partly scale resolving simulation by resolving unsteady perturbation dynamics on given mesh forced by 3+1-D synthetic turbulence (flowacoustic feedback becomes feasible) Goal: Smooth transition between regions with deterministic source mode and partly scale resolving simulation use LEE (first step) and Navier-Stokes equations in perturbation form How to couple 3+1-D synthetic turbulence with equations? Hydrodynamic instabilities possible Linearized Euler Equations (LEE) Non-linear Sound Sources CFD / RANS 3+1-D Synthetic Turbulence
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