Review and analysis of the DNW/model 360 rotor acoustic data base

Cover of: Review and analysis of the DNW/model 360 rotor acoustic data base |

Published by National Aeronautics and Space Administration, Ames Research Center, US Army Aviation Systems Command, Aviation Research and Technology Activity, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va .

Written in English

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Subjects:

  • Rotors (Helicopters) -- Noise -- Databases.,
  • Aeroacoustics.,
  • Blade-vortex interaction.,
  • Data bases.,
  • Noise reduction.,
  • Performance prediction.,
  • Rotor blades (Turbomachinery)

Edition Notes

Book details

StatementR.A. Zinner and D.A. Boxwell, R.H. Spencer.
GenreDatabases.
SeriesNASA technical memorandum -- 102253., USAAVSCOM technical memorandum -- 89-A-002., AVSCOM technical memorandum -- 89-A-002.
ContributionsBoxwell, D. A., Spencer, R. H., Ames Research Center., United States. Army Aviation Research and Technology Activity.
The Physical Object
FormatMicroform
Pagination22 p.
Number of Pages22
ID Numbers
Open LibraryOL16139115M

Download Review and analysis of the DNW/model 360 rotor acoustic data base

Twenty-six microphones were positioned around the azimuth to collect acoustic data for approximately different test conditions. A dynamically scaled, blade- pressure-instrumented model of the forward rotor of the BH helicopter simultaneously provided blade pressures for correlation with the acoustic Size: 1MB.

Review and Analysis of the DNW/Model Rotor Acoustic Data Base R. Zinner and D. Boxwell, Aeroflightdynamics Directorate, U.S. Army Aviation Research and Technology Activity, Ames Research Center, Moffett Field, California R. Spencer, Boeing Helicopters, Philadelphia, Pennsylvania November National Aeronautics and.

A comprehensive model rotor aeroacoustic data base was collected in a large anechoic wind tunnel in Twenty-six microphones were positioned around the. Get this from a library. Review and analysis of the DNW/model rotor acoustic data base. [R A Zinner; D A Boxwell; R H Spencer; Ames Research Center.; United States.

Army Aviation Research and Technology Activity.]. A dynamically scaled, blade-pressure-instrumented model of the forward rotor of the BH helicopter simultaneously provided blade pressures for correlation with the acoustic data.

High-speed impulsive noise, blade-vortex interaction noise, low-frequency noise, and broadband noise were all captured in this extensive data : D. Boxwell, R. Spencer and R. Zinner. Within the framework of a major European co-operative research project on rotorcraft aerodynamics and acoustics (Helishape), a parametric model rotor test was conducted in the open test section of the DNW using DLR's MWM test rig, and a highly instrumented model of a fully articulated ECF rotor equipped with blades of advanced design with two Cited by: D.

Boxwell's 17 research works with citations and reads, including: Model Helicopter Rotor Aerodynamics and Acoustics As Measured in Two Anechoic Wind Tunnels. A three person CIE Review Panel meet from Septemberat Marine Acoustic Inc.’s offices in Arlington VA.

The purpose of the meeting was to review Marine Acoustic Inc.’s Acoustic Integration Model (AIM). The review was initiated by NMFS who required an independent peer review of AIM. AIM is a software package. Near Field Acoustic Test on a Low Boom Configuration in Langley's 4 x 4 Wind Tunnel (Invited) of the DNW/Model rotor acoustic data base.

sources in a propfan model by analysis. Munjal [2] proposed an elementary theoretical model to design acoustic enclosures. His model is based on Insertion loss, defined as reduction of Sound Pressure Level (SPL) at the receiver due to location of the source (machine) in an acoustic enclosure.

He also provided data for random incidence transmission loss of typical partition walls. Review And Analysis Of The DNW/Model Rotor Acoustic Data Base MAT advancing tip Mach number Mtj hover tip Mach number.

MHN oM nominal hover tip Mach number, fier/filters, 32 Preston GMSH sample and hold amplifiers, Review and Analysis of the DNW/Model Rotor Acoustic Data November Base 6 Performing Organizaion Code 7. Boxwell DA, Schmitz FH, Splettstoesser WR, Schultz K-J, Lewy S, Caplot M () A comparison of the acoustic and aerodynamic measurements of a model rotor tested in two anechoic wind tunnels.

Paper No 38, 12th European Rotorcraft Forum, Garmisch-Partenkirchen Google Scholar. In earlyinitial acoustic results were obtained from a HHC experiment conducted in the DNW closed test section with the objective of demonstrating the effectiveness of higher harmonic blade pitch control to reduce rotor BVI impulsive noise.(37) This test was performed as part of a HHC demonstration experiment of DLR on reduction of rotor Cited by: Rotor construction Slip Rotor induced e.m.f., current and torque Rotor currents and torque – small slip Rotor currents and torque – large slip Influence of Rotor Current on Flux Reduction of flux by rotor current Stator Current-Speed Characteristics Review Questions 6 OPERATING CHARACTERISTICS OF.

The experimental data was obtained by ATIC model rotor tests [9–11] at the German Dutch Windtunnel (DNW). The comparisons are performed at 12 azimuth-wise positions at r/R= The quantities r and R are span-wise station and rotor radius, respectively.

The agreement is good in every azimuth position. Package ‘VTrack’ Febru Type Package Title A Collection of Tools for the Analysis of Remote Acoustic Telemetry Data Version Date Author Ross G. Dwyer, Mathew E. Watts, Hamish A. Campbell, Vinay Udyawer & Craig E. Franklin Maintainer Ross Dwyer File Size: KB.

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pany, in a test involving a 1/5 size, dynamically scaled 6) evaluate the acoustic and performance model of the Boeing Model rotor. Simultaneous characteristics of a main rotor with a blade pressure and acoustic data were acquired over BERP-planform tip.

a full matrix of test conditions (Refs. 5,6).Cited by: Building DNN Acoustic Models for Large Vocabulary Speech Recognition Andrew L. Maas, Peng Qi, Ziang Xie, Awni Y. Hannun, Christopher T.

Lengerich, Daniel Jurafsky, Andrew Y. Ng, Abstract—Deep neural networks (DNNs) are now a central component of nearly all state-of-the-art speech recognition by: using a scaled isolated tiltrotor model. Acoustic data were acquired using an in-flow microphone wing traversed beneath the model to map the directivity of the near-field acoustic radiation of the rotor for a parametric variation of rotor angle-of-attack, tunnel speed, and rotor thrust.

Acoustic metric data wereFile Size: 1MB. Rotordynamic Analysis of Bolted Disk-Drum Rotor with Contact Nonlinearity Manuscript id. Page 2 joint on dynamic behavior of rotor-bearing system and compare the findings with the results obtained from theFile Size: 1MB.

illustrated with prediction examples for a model rotor in a wind tunnel, a rotorcraft in flight and for a notional coaxial rotor configuration. For the model rotor illustration, predicted rotor airloads and acoustics for a BO model rotor are computed and the results are compared to test data from HART-II for the non-HHC baseline by: 7.

Review and Analysis of the DNW/Model (Duits-Nederlandse Windtunnel) Rotor Acoustic Data Base [R. Zinner] on *FREE* shipping on qualifying offers. Omschrijving. Vier technici bereiden een test voor in de Duits-Nederlandse Windtunnel. Find The Right Part for Your Ford Vehicle. Search by VIN, Vehicle, or Part #.

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Model Wind Rotors and Experiments. The diameter of the front wind rotor is d F = mm, and the rear is d R = mm, where the diameter ratio D RF [=d R / d F] is The axial distance between the front and the rear wind rotors is l = 40 mm at the twist centres.

The front and the rear bade numbers are Z F = 3, Z R = 5. These dimensions Author: K. Kubo, T. Kanemoto. thod. Both source data and propagation model are new. The new source model distin-guishes between tyre/road noise and propulsion noise, and the new propagation model al-lows computations for a variety of weather conditions.

Nord Road is significantly better than the old method. It can handle computation inFile Size: KB. Acoustic data are presented from a percent-scale model of the four-bladed BO helicopter main rotor, tested in a large aeroacoustic wind tunnel.

Rotor blade-vortex interaction (BVI) noise data in the low-speed flight range were acquired using a traversing in-flow microphone array. This book demonstrates the implementation of an improved adaptive Wiener filter on Texas Instruments TMS C DSK board. A performance comparison of an improved adaptive Wiener filter with Lee's adaptive Wiener filter is illustrated.

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