NASA’s Acoustic Modeling and Simulation Tools for ... · NASA’s Acoustic Modeling and...
Transcript of NASA’s Acoustic Modeling and Simulation Tools for ... · NASA’s Acoustic Modeling and...
-
NASAs Acoustic Modeling and Simulation Tools for Perception-Influenced Design of
Urban eVTOL Systems
Dr. Stephen A. RizziSenior Researcher for Aeroacoustics
NASA Langley Research Center
Uber Elevate SummitApril 25-27, 2017
Dallas, TX
-
Outline
Perception-Influenced Design Auralization
Source-Path-Receiver Source Noise Description
Demonstrations Volocopter-like Multi-Rotor eVTOL, Tilt-Wing eVTOL Installation Effects Ambient Noise
Detection and Annoyance Predictions and Lab Studies
Uber Elevate Summit 2
-
Human response to aircraft community noise is a complex perception phenomenon that is a function of both acoustic and non-acoustic factors.
The aircraft vehicle design process requires a multi-disciplinary approach to achieve a set of design goals that typically include performance, safety, energy consumption, and noise. Noise goals usually specified in terms of certification
metrics, which may not fully reflect acoustic factors related to human response, nor are intended to reflect non-acoustic factors.
ICAO noise certification requirements are part of a balanced approach which strives to manage aircraft noise in the most cost-effective manner.
Background
Uber Elevate Summit 3
-
Multiple FidelitySystem Noise
Prediction
MDAOEnvironment
AeroPerformance
Energy
Safety
.
.
.
Metrics-Driven Design Process for Noise
Source NoiseModels & Reduction
PropulsionAirframe
Aeroacoustics
Validated AeroacousticTools & Methods for
Low Noise
4
-
How well do certification metrics reflect human response to these systems?
0 4 8 12 16-0.03
-0.02
-0.01
0
0.01
0.02
0.03
Time (s)
Am
plitu
de
Uber Elevate Summit 5
-
MDAOEnvironment
Perception-Influenced (Aircraft Vehicle) Design
Source NoiseModels & Reduction
PropulsionAirframe
Aeroacoustics
Multiple FidelitySystem Noise
PredictionAuralization
Human Response
and Metrics
Human PerceptionValidated Aeroacoustic
Tools & Methods forLow Noise
AeroPerformance
Energy
Safety
.
.
.
Perception-Influenced Design Design aircraft to achieve reduced community noise impact by simultaneously meeting noise certification and other design requirements, as well as other acoustic requirements which directly address human response.
6
Auralization offers the means to systematically assess benefits of future aircraft noise reduction technologies, configurations, and operations, through subjective testing.
-
Curved path
Synthesis here
Synthesis here
Path modeling includes:
1) Doppler shift/absolute delay2) Atmospheric absorption3) Spreading loss
Auralization Process: Source Path Receiver
(Not to scale)
4) Ground plane
Uber Elevate Summit 7
The NASA Auralization Framework (NAF) performs these functions.
-
Source Noise Description
High Fidelity Analyses OVERFLOW, FUN3D CFD
8
Ground Testing Low Speed Aeroacoustic Wind Tunnel Anechoic chambers
Flight Testing Rotorcraft & UAVs
-
Low-Fidelity Codes for Propeller/Rotor Noise ANOPP Propeller Analysis System
Tonal loading and thickness noise components
Broadband Acoustic Rotor Code (BARC) Airfoil self-noise components
Uber Elevate Summit 9
Source Noise Description
-
NASA Volocopter-like* eVTOL Multi-Rotor
* Based on information in The Volocopter flies! And is Ready to Take the Next Step to Urban Mobility, Florian Reuter, e-volo GmbH, NASA ODM Workshop, Hartford, CT, 29 Sept 2016.
Uber Elevate Summit 10
Blade Design Used XROTORs minimum induced loss design method (18) 1.8m dia. 2-blade Clark Y airfoil
8.8 pitch at 75% r/R
Tip speed 160 m/s 1700 RPM, BPF 57 Hz Total thrust: 650 kg Power: 3.85 kW/rotor Figure of Merit: 0.69
Vehicle 2 passenger MTOM: 450 kg
-
NASA eVTOL Tilt-Wing Concept
Uber Elevate Summit 11
Blade Design Based on multi-rotor design (8) 3m dia. 4-blade Clark Y airfoil
18.8 pitch at 75% r/R
Tip speed 140 m/s 891 RPM, BPF 59 Hz Total thrust: 1800 kg Power: 34.1 kW/rotor Figure of Merit: 0.73
Vehicle 4 passenger MTOM: 1250 kg 6 props on front wing 2 props on tail
-
Vertical Take-Off Scenario Multi-Rotor
Uber Elevate Summit 12
Acoustic Modeling Zero angle of attack Tonal components only Rotors RPM - synchronized
30m
75m
Trajectory 10s hold at ground, 2.5 m/s rise to 75m Sideline observer at 30m
Time (s)
L A(d
B)
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60
70
80
90
SynchR22
-
Uber Elevate Summit 13
Acoustic Modeling Zero angle of attack Tonal components only Rotors RPM 2% variation
30m
75m
Trajectory 10s hold at ground, 2.5 m/s rise to 75m Sideline observer at 30m
Time (s)
L A(d
B)
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60
70
80
90
DFSynchR22
Vertical Take-Off Scenario Multi-Rotor
-
GROUND TESTING
Determine contributions of rotor and rotor-airframe interactions to radiated noise for simple vehicle configurations
Rotor and airframe support stands- Physically separate from one another- Able to vary rotor tip separation distance ()- Airframes of constant and variable cross-
section considered- ref 1
Results show- Harmonically rich for small rotor tip clearances () - Case of = 0.5 nearly identical to case of
isolated rotor
POC: Nik Zawodny Uber Elevate Summit 14
Investigation of Rotor-Airframe Interaction Noise Associated with Small-Scale Rotary-Wing Unmanned Aircraft Systems, Zawodny, Boyd, 73rd AHS Forum, Ft. Worth, TX, May 9-11, 2017.
SPL (
dB)
-
POC: Nik Zawodny
GROUND TESTING
Uber Elevate Summit 15
SPL
(dB)
-
POC: Nik Zawodny
GROUND TESTING
Uber Elevate Summit 16
SPL
(dB)
-
POC: Nik Zawodny
GROUND TESTING
Uber Elevate Summit 17
SPL
(dB)
-
POC: Nik Zawodny
GROUND TESTING
Uber Elevate Summit 18
SPL
(dB)
-
Uber Elevate Summit 19
Acoustic Modeling Zero angle of attack Tonal components only Rotors RPM 2% variation Rotor Structure Interaction
30m
75m
Trajectory 10s hold at ground, 2.5 m/s rise to 75m Sideline observer at 30m
Time (s)
L A(d
B)
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60
70
80
90
DF+RSIDFSynchR22
Vertical Take-Off Scenario Multi-Rotor
10dBA lower than R22 (half as loud)
-
Uber Elevate Summit 20
Acoustic Modeling Zero angle of attack Tonal components only Rotors RPM 2% variation Rotor Structure Interaction
30m
75m
Trajectory 10s hold at ground, 2.5 m/s rise to 75m Sideline observer at 30m
Vertical Take-Off Scenario Tilt-Wing
Time (s)
L A(d
B)
0 5 10 15 20 25 30 35 400
10
20
30
40
50
60
70
80
90
DF+RSIDFSynchR22
10dBA lower than multi-rotor (half as loud)20dBA lower than R22 (quarter as loud)
-
Ambient Sound
Uber Elevate Summit 21
US Bureau of Transportation Statistics
A-weighted 24-hour LAeq (dBA)You are here
55 dBA
But wish you were here38 dBA
-
Ambient Sound
Uber Elevate Summit 22Frequency (Hz)
SPL
(dB
)
200 400 600 800 10000
5
10
15
20
25
30
35
40
45
50City (55 dBA Leq)Park (38 dBA Leq)Pure Tone Threshold
-
The Full Monty - City Scenario
Uber Elevate Summit 23
-
The Full Monty - Park Scenario
Uber Elevate Summit 24
-
Detection ICHIN* Version 7 Predictions
Uber Elevate Summit 25
Multi-Rotor Tilt-Wing
Normalized Range
Prob
abili
tyof
Det
e cti o
n(%
)
0 0.2 0.4 0.6 0.8 10
20
40
60
80
100City AmbientPark Ambient
0.2 0.45
Normalized Range
Prob
abili
tyof
Det
ectio
n(%
)
0 0.2 0.4 0.6 0.8 10
20
40
60
80
100
City AmbientPark Ambient
0.37 1.0
Must take into account the vehicle and its operating environment toeffectively reduce audibility.
In the city, detection is at the BPF for both vehicles. In the park, detection is at the 2nd and 3rd harmonics for both vehicles.
* I Can Hear it Now (Part of APET)
-
Emission Distance (normalized by sample x50)
Prob
abili
ty(#
with
in
/#su
rere
spon
ses)
00.511.520
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
| | 15| | 22.5| | 30
Detection Lab Studies
26
NASA Langley Exterior Effects Room
Normalized Emission Distance
Prob
abili
ty(#
Sure
s/#
Tota
lSur
es)
00.511.50
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
Subject Dataxx50Probit Fit
Rotorcraft Fly-In Detection
Rotorcraft Fly-In Localization
A Laboratory Method for Assessing Audibility and Localization of Rotorcraft Fly-In Noise, Rizzi et al., 73rd AHS Forum, Ft. Worth, May 9-11, 2017.
-
Time-Varying Noise Metrics
Uber Elevate Summit 27
Loudness Roughness
0 10 20 30 40
Time (s)
0
5
10
15
20
25
30
35
Loud
ness
(son
e)
Multi-Rotor: N5=26.59 sone
Tilt-Wing: N5=14.98 sone
0 10 20 30 40
Time (s)
0
0.5
1
1.5
Rou
ghne
ss (a
sper
)
Multi-Rotor: R5= 1.30 asper
Tilt-Wing: R5= 0.96 asper
0 10 20 30 40
Time (s)
0
0.01
0.02
0.03
0.04
0.05
0.06
0.07
Fluc
tuat
ion
Stre
ngth
(vac
il)
Multi-Rotor: FS5= 0.03 vacil
Tilt-Wing: FS5= 0.02 vacil
Fluctuation Strength
A-Weighted Level Sharpness Tonality
0 10 20 30 40
Time (s)
0
20
40
60
80
LA
S (d
B)
Multi-Rotor: LA S
5= 74 dB
Tilt-Wing: L A S5= 64 dB
0 10 20 30 40
Time (s)
0
0.1
0.2
0.3
0.4
0.5
0.6
Shar
pnes
s (a
cum
)
Multi-Rotor: S5= 0.42 acum
Tilt-Wing: S5= 0.41 acum
0 10 20 30 40
Time (s)
0
0.2
0.4
0.6
0.8
1
1.2
Tona
lity
(tu)
Multi-Rotor: T5= 0.95 tu
Tilt-Wing: T5= 1.03 tu
-
Zwicker & Fastl Psychoacoustic Annoyance
Uber Elevate Summit 28
0 10 20 30 40
Time (s)
0
10
20
30
40
50Ps
ycho
acou
stic
Ann
oyan
ce
Multi-Rotor: PA5=37.88
Tilt-Wing: PA5=20.43
-
Annoyance Lab Studies
29
A Psychoacoustic Evaluation of Noise Signatures from Advanced Civil Transport Aircraft, Rizzi, Christian, 22nd AIAA/CEAS Aeroacoustics Conference, Lyon, France, May 31, 2016, AIAA-2016-2907.
Initial Investigation into the Psychoacoustic Properties of Small Unmanned Aerial Vehicle Noise, Christian, Cabell, AIAA Aviation 2017
LTA Ref
SA Ref T+W160
HWB301
Comparison of EPNL reduction
EPN
LR
educ
tion
(EPN
dB)
T+W
160-
GTF
-ITD
Appr
oach
T+W
160-
GTF
-ITD
Side
line
HW
B301
-GTF
-ITD
Appr
oach
HW
B301
-GTF
-ITD
Side
line
0
2.5
5
7.5
10
12.5
15System Noise PredictionWith Adjustment
SA LTA
Qui
eter
-
Perception-influenced design is made possible through the use of validated noise prediction models supporting auralization and models for human response (e.g., detection and annoyance).
NASA has unique capabilities in the areas of systems analysis, system noise prediction inclusive of important propulsion airframe aeroacoustics, auralization, and psychoacoustic testing. These capabilities were demonstrated on two relevant
urban eVTOL concepts. Come and see us at our interactive demo where you can
experience the eVTOL and other aircraft auralizations in an immersive environment.
Conclusions
Uber Elevate Summit 30
-
Movies and sounds are available for download at:
http://stabserv.larc.nasa.gov/flyover/
Uber Elevate Summit 31
-
ContributorsAric Aumann (SAIC) Auralization and interactive demoJon Levy, Eric Fay, Josh Sams (AMA Studios) 3D graphicsDan Palumbo (AMA) AuralizationMichael Patterson (NASA) Propeller/rotor designNoah Schiller (NASA) AuralizationCharlie Smith (AMA) Detection analysisNik Zawodny (NASA) Propulsion Airframe Aeroacoustics
Acknowledgments
This research was supported by the NASA Aeronautics Research MissionDirectorate (ARMD), Advanced Air Vehicles Program (AAVP), RevolutionaryVertical Lift Technology (RVLT) Project, and the Transformative AeronauticsConcept Program (TACP), Transformational Tools and Technologies (TTT) Project.
Uber Elevate Summit 32
-
Thank You
-
1. Rizzi, S.A., Toward reduced aircraft community noise impact via a perception-influenced design approach (Keynote), InterNoise 2016, Hamburg, Germany, August 22-24, 2016.
2. Rafaelof, M., A model to gauge the annoyance due to arbitrary time-varying sound, Noise-Con 2016, Providence, RI, June 13-15, 2016.
3. Christian, A. and Lawrence, J., Initial development of a quadcopter simulation environment for auralization, 72nd AHS Forum, West Palm Beach, FL, May 17-19, 2016.
4. Rizzi, S.A. and Christian, A., "A psychoacoustic evaluation of noise signatures from advanced civil transport aircraft," 22nd AIAA/CEAS Aeroacoustics Conference, AIAA 2016-2907, Lyon, France, May 30 - June 1, 2016.
5. Rizzi, S.A., Burley, C.L., and Thomas, R.H., "Auralization of NASA N+2 aircraft concepts from system noise predictions," 22nd AIAA/CEAS Aeroacoustics Conference, AIAA 2016-2906, Lyon, France, May 30 - June 1, 2016.
6. Rizzi, S.A., Stephens, D.B., Berton, J.J., Van Zante, D.E., Wojno, J.P., and Goerig, T.W., "Auralization of flyover noise from open rotor engines using model scale test data," AIAA Journal of Aircraft, Vol. 53, No. 1, pp. 117-128, 2016.
7. Rizzi, S.A. and Christian, A., A method for simulation of rotorcraft fly-in noise for human response studies, InterNoise 2015, San Francisco, CA, August 9-12, 2015.
8. Christian, A., Boyd Jr., D.D., Zawodny, N.S., and Rizzi, S.A., Auralization of tonal rotor noise components of a quadcopter flyover, InterNoise 2015, San Francisco, CA, August 9-12, 2015.
Bibliography
34
-
9. Aumann, A.R., Tuttle, B.C., Chapin, W.L., and Rizzi, S.A., The NASA Auralization Framework and Plugin Architecture, InterNoise 2015, San Francisco, CA, August 9-12, 2015.
10. Rizzi, S.A., Lopes, L.V., and Burley, C.L., NASA's aeroacoustic tools and methods for analysis of aircraft noise, AIAA SciTech 2015, Kissimmee, FL, January 5-9, 2015 (Abstract Only).
11. Rizzi, S.A., Palumbo, D.L., Hardwick, J.R., and Christian, A., Recent advances in aircraft source noise synthesis, 168th Meeting of the Acoustical Society of America, Indianapolis, IN, October 27-31, 2014.
12. Aumann, A.R., Chapin, W.L., and Rizzi, S.A., An open architecture for auralization of dynamic soundscapes, 168th Meeting of the Acoustical Society of America, Indianapolis, IN, October 27-31, 2014.
13. Tuttle, B.C., and Rizzi, S.A., Simulation of excess ground attenuation for aircraft flyover noise synthesis, 168th Meeting of the Acoustical Society of America, Indianapolis, IN, October 27-31, 2014.
14. Hardwick, J.R., Christian, A., and Rizzi, S.A., Evaluation of the perceptual fidelity of a novel rotorcraft noise synthesis technique, 168th Meeting of the Acoustical Society of America, Indianapolis, IN, October 27-31, 2014.
15. Rizzi, S.A., Aumann, A.R., Lopes, L.V., and Burley, C.L., Auralization of hybrid wing body aircraft flyover noise from system noise predictions, AIAA Journal of Aircraft, Vol. 51, No. 6, pp. 1914-1926, 2014.
Bibliography
35
-
16. Arntzen, M., Rizzi, S.A., Visser, H.G., and Simons, D.G., A framework for simulation of aircraft flyover noise through a non-standard atmosphere, AIAA Journal of Aircraft, Vol. 51, No. 3, pp. 956-966, 2014.
17. Rizzi, S.A., Stephens, D.B., Berton, J.J., Van Zante, D.E., Wojno, J.P., and Goerig, T.W., Auralization of flyover noise from open rotor engines using model scale test data, 20th AIAA/CEAS Aeroacoustics Conference, AIAA-2014-2750, Atlanta, GA, June 16-20, 2014.
18. Palumbo, D.L., Nark, D.M., Burley, C.L., and Rizzi, S.A., Aural effects of distributed propulsion, 14th AIAA Aviation Technology, Integration, and Operations Conference, Atlanta, GA, June 16-20, 2014 (Abstract Only).
19. Rizzi, S.A., Lopes Jr, V., Burley, C.L., and Aumann, A.R., Auralization architectures for NASAs next generation aircraft noise prediction program, Noise-Con 2013, Denver, CO, August 26-28, 2013.
20. Okcu, S., Rathsam, J., and Rizzi, S.A., Psychoacoustic analysis of synthesized jet noise, Noise-Con 2013, Denver, CO, August 26-28, 2013.
21. Rizzi, S.A., An overview of virtual acoustic simulation of aircraft flyover noise (Invited Plenary), Structural Dynamics: Recent Advances, Proceedings of the 11th International Conference, Pisa, Italy, 2013.
22. Faller II, K.J., Rizzi, S.A., and Aumann, A.R., Acoustic performance of a real-time three-dimensional sound-reproduction system, NASA TM-2013-218004, June 2013.
Bibliography
36
-
23. Rizzi, S.A., Aumann, A.R., Lopes, L.V., and Burley, C.L., Auralization of hybrid wing body aircraft flyover noise from system noise predictions, 51st AIAA Aerospace Sciences Meeting, AIAA-2013-0542, Grapevine, TX, 2013.
24. Okcu, S., Allen, M.P. and Rizzi, S.A., Psychoacoustic assessment of a new aircraft engine fan noise synthesis method, 164th Meeting of the Acoustical Society of America, Kansas City, MO, 2012.
25. Arntzen, M., Rizzi, S.A., Visser, H.G., and Simons, D.G., A framework for simulation of aircraft flyover noise through a non-standard atmosphere, 18th AIAA/CEAS Aeroacoustics Conference, AIAA-2012-2079, Colorado Springs, CO, 2012.
26. Allen, M.P., Rizzi, S.A., Burdisso, R., and Okcu, S., Analysis and synthesis of tonal aircraft noise sources, 18th AIAA/CEAS Aeroacoustics Conference, AIAA-2012-2078, Colorado Springs, CO, 2012.
27. Rizzi, S.A., Aumann, A.R., Allen, M.P., Burdisso, R., and Faller II, K.J., Simulation of rotary and fixed wing flyover noise for subjective assessments, (Invited), 161st Meeting of the Acoustical Society of America, Seattle, WA, May 23-27, 2011 (Abstract Only).
28. Faller II, K.J., Rizzi, S.A., and Aumann, A.R., Acoustic performance of an installed real-time three-dimensional audio system - Part II, 161st Meeting of the Acoustical Society of America, Seattle, WA, May 23-27, 2011 (Abstract Only).
Bibliography
37
-
29. Faller II, K.J., Rizzi, S.A., Schiller, N., Cabell, R.H., Klos, J., Chapin, W.L., and Aumann, A.R., Acoustic performance of an installed real-time three-dimensional audio system, Proceedings of Meetings on Acoustics (POMA), Acoustical Society of America, Vol. 11, pp. 1-13, 2010.
30. Faller II, K.J., Rizzi, S.A., Schiller, N., Cabell, R.H., Klos, J., Chapin, W.L., and Surucu, F., Acoustic performance of an installed real-time three-dimensional audio system, 2ndPan-American/Iberian Meeting on Acoustics, 160th Meeting of the Acoustical Society of America, Cancun, Mexico, 2010 (Abstract Only).
31. Faller II, K.J., Rizzi, S.A., Klos, J., Chapin, W.L., Surucu, F., and Aumann, A.R., Acoustic calibration of the Exterior Effects Room at the NASA Langley Research Center, Proceedings of Meetings on Acoustics (POMA), Acoustical Society of America, Vol. 9, No. 015004, pp. 1-10, 2010.
32. Faller II, K.J., Rizzi, S.A., Klos, J., Chapin, W.L., Surucu, F., and Aumann, A.R., Acoustic calibration of the Exterior Effects Room at the NASA Langley Research Center, 159thMeeting of the Acoustical Society of America and Noise-Con 2010, Baltimore, MD, April 19-23, 2010 (Abstract Only).
33. Rizzi, S.A., Sullivan, B.M., and Aumann, A.R., Recent developments in aircraft flyover noise simulation at NASA Langley Research Center, NATO Research and Technology Agency AVT-158 Environmental Noise Issues Associated with Gas Turbine Powered Military Vehicles Specialists Meeting, NATO RTA Applied Vehicle Technology Panel, Paper 17, pp. 14, Montreal, Canada, 2008.
Bibliography
38
-
34. Rizzi, S.A. and Sullivan, B.M., Synthesis of Virtual Environments for Aircraft Community Noise Impact Studies, Proceedings of the 11th AIAA/CEAS Aeroacoustics Conference, AIAA-2005-2983, Monterey, CA, May 2005.
35. Rizzi, S.A., Three-Dimensional Audio Client Library, NASA Tech Briefs, Vol. 29, No. 2, 2005, pp. 45.
36. Sullivan, B.M. and Rizzi, S.A., Further Developments in Aircraft Flyover Noise Synthesis and Propagation, 148th Meeting of the Acoustical Society of America, San Diego, CA, November 15-19, 2004 (Abstract Only).
37. Grosveld, F.W., Sullivan, B.M., and Rizzi, S.A., Temporal Characterization of Aircraft Noise Sources, Proceedings of the 42nd AIAA Aerospace Sciences Meeting, AIAA-2004-1029, Reno, NV, January 5-8, 2004.
38. Rizzi, S.A., Sullivan, B.M., and Cook, B.A., Signal Processing for Aircraft Noise (Invited), 146th Meeting of the Acoustical Society of America, Austin, TX, November 10-14, 2003 (Abstract Only).
39. Rizzi, S.A., Sullivan, B.M., and Sandridge, C.A., A Three-Dimensional Virtual Simulator for Aircraft Flyover Presentation, Proceedings of the 2003 International Conference on Auditory Display, Boston, MA, 2003.
40. Rizzi, S.A. and Sullivan, B.M., Prediction-Based Aircraft Flyover Noise Synthesis, 145thMeeting of the Acoustical Society of America, Nashville, TN, April 28 May 2, 2003 (Abstract Only).
Bibliography
39
NASAs Acoustic Modeling and Simulation Tools for Perception-Influenced Design of Urban eVTOL SystemsOutlineBackgroundMetrics-Driven Design Process for NoiseHow well do certification metrics reflect human response to these systems?Perception-Influenced (Aircraft Vehicle) DesignAuralization Process: Source Path ReceiverSource Noise DescriptionSource Noise DescriptionNASA Volocopter-like* eVTOL Multi-RotorNASA eVTOL Tilt-Wing ConceptVertical Take-Off Scenario Multi-RotorSlide Number 13GROUND TESTINGGROUND TESTINGGROUND TESTINGGROUND TESTINGGROUND TESTINGSlide Number 19Slide Number 20Ambient SoundAmbient SoundThe Full Monty - City ScenarioThe Full Monty - Park ScenarioDetection ICHIN* Version 7 PredictionsDetection Lab StudiesTime-Varying Noise MetricsZwicker & Fastl Psychoacoustic AnnoyanceAnnoyance Lab StudiesConclusionsSlide Number 31AcknowledgmentsSlide Number 33BibliographyBibliographyBibliographyBibliographyBibliographyBibliography