Airframe Noise Study of a CRJ-700 Aircraft Model in the NASA Ames 7- by 10- Foot Wind Tunnnel No. 1

Soderman, P. T.; Kafyeke, F.; Burnside, Nathan; Chandrasekharan, Reuben; Jaeger, Stephen; Boudreau, Josee

doi:10.2514/6.2002-2406

Cited by 19 publications

(1 citation statement)

References 10 publications

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“…Most often, airframe noise sources can be modeled as unsteady forces acting perpendicular to a surface, so called dipole sources. [15][16][17][18] Thus in this paper, these kinds of sources are considered to be the main contributing sources from the half model in the test section. As can be derived from the Ffowcs Williams-Hawkings solution of the acoustic analogy with surface sources (see Crighton et al 19 , p.334ff; or as has been shown by Curle 20 in a similar manner), the sound generated in terms of the mean-squared density fluctuations ρ in the far-field for compact b dipole sources at low Mach numbers is of order…”

Section: B Condition Correctionsmentioning

confidence: 99%

Microphone Array Measurement in European Transonic Wind Tunnel at Flight Reynolds Numbers

Ahlefeldt

2017

AIAA Journal

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This paper presents an experimental investigation of small-scale model airframe noise at various Reynolds numbers up to the real-flight case. The study consists of data acquired with a microphone array in the European Transonic Windtunnel (ETW). The advantage of the ETW is to enable testing simultaneously at cryogenic temperatures and increased pressure levels, which extends the range of achievable Reynolds numbers up to those pertaining to full-scale flight conditions. At the German Aerospace Center (DLR), the microphone-array measurement technique has been further developed to perform measurements under combined cryogenic and pressurized conditions. For this purpose, a microphone-array consisting of 96 microphones was designed and constructed. In this paper, aeroacoustic results are presented for various Reynolds numbers up to the real-flight case on an Airbus K3DY half-model of scale 1:13.6. The results showed significant Reynolds number and Mach number dependency for various sources. Of particular note are various dominant sources appearing on the flap at real-flight Reynolds numbers. To the authors knowledge, this is the first time that airframe noise data for a small-scale model have been acquired at real-flight Reynolds numbers.Nomenclature * Research Associate, German Aerospace Center. Associated member AIAA.

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Section: B Condition Correctionsmentioning

confidence: 99%

Microphone Array Measurement in European Transonic Wind Tunnel at Flight Reynolds Numbers

Ahlefeldt

2017

AIAA Journal

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Near-field fluctuations and far-field noise of a three-element airfoil system by a discrete vortex method

Zheng

Tan

2010

Applied Mathematics and Computation

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An artificial neural network approach for aerodynamic performance retention in airframe noise reduction design of a 3D swept wing model

Tao

Sun

2016

Chinese Journal of Aeronautics

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Airframe Noise Study of a CRJ-700 Aircraft Model in the NASA Ames 7- by 10- Foot Wind Tunnnel No. 1

Cited by 19 publications

References 10 publications

Microphone Array Measurement in European Transonic Wind Tunnel at Flight Reynolds Numbers

Microphone Array Measurement in European Transonic Wind Tunnel at Flight Reynolds Numbers

Near-field fluctuations and far-field noise of a three-element airfoil system by a discrete vortex method

An artificial neural network approach for aerodynamic performance retention in airframe noise reduction design of a 3D swept wing model

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