Phased Acoustic Array Measurements of a 5.75% Hybrid Wing body Aircraft (Invited)

2016 ◽  
Author(s):  
Nathan J. Burnside ◽  
William C. Horne ◽  
Kevin R. Elmer ◽  
Rui Cheng ◽  
Leon Brusniak
Keyword(s):  
Array Measurements ◽  
Acoustic Array

Phased acoustic array measurements of a 5.75% hybrid wing body aircraft

2017 ◽  
Vol 16 (4-5) ◽  
pp. 326-357
Author(s):  
Nathan J Burnside ◽  
William C Horne ◽  
Kevin R Elmer ◽  
Rui Cheng ◽  
Leon Brusniak
Keyword(s):  
Wind Tunnel ◽  
Microphone Array ◽  
Leading Edge ◽  
Noise Model ◽  
Acoustic Measurements ◽  
Frequency Range ◽  
High Lift ◽  
Array Measurements ◽  
Individual Support ◽  
Acoustic Array

Detailed acoustic measurements of the noise from the leading-edge Krueger flap of a 5.75% hybrid wing body aircraft model were acquired with a traversing phased microphone array in the Arnold Engineering Development Complex NFAC 40- by 80-foot wind tunnel. The spatial resolution of the array was sufficient to distinguish between individual support brackets over the full-scale frequency range of 100 to 2875 Hz. For conditions representative of landing and take-off configuration, the noise from the brackets dominated other sources near the leading edge. Inclusion of flight-like brackets for select conditions highlights the importance of including the correct number of leading-edge high-lift device brackets with sufficient scale and fidelity. These measurements support the development of a Krueger noise model which includes cove and bracket noise.

Field Statistics of Acoustic Array of the Equipment for Remote Sensing of the Atmosphere

2008 ◽  
Vol 67 (4) ◽  
pp. 293-308 ◽  
Author(s):  
Ya. S. Shifrin ◽  
Y. N. Ulyanov ◽  
N. G. Maksimova
Keyword(s):  
Remote Sensing ◽  
Acoustic Array

Dynamics of Acoustic Array Cables.

1995 ◽  
Author(s):  
William S. Hodgkiss
Keyword(s):  
Acoustic Array

scholarly journals Aeroacoustic noise reduction by application of end plates on wall-mounted finite airfoils

2021 ◽  
Vol 62 (5) ◽  
Author(s):  
Erik Schneehagen ◽  
Thomas F. Geyer ◽  
Ennes Sarradj ◽  
Danielle J. Moreau
Keyword(s):  
Noise Reduction ◽  
Microphone Array ◽  
Boundary Layer Transition ◽  
Tip Vortex ◽  
Layer Transition ◽  
Aeroacoustic Noise ◽  
End Plate ◽  
Array Measurements ◽  
Field Noise ◽  
Naca 0012

Abstract One known method to reduce vortex shedding from the tip of a blade is the use of end plates or winglets. Although the aerodynamic impact of such end plates has been investigated in the past, no studies exist on the effect of such end plates on the far-field noise. The aeroacoustic noise reduction of three different end-plate geometries is experimentally investigated. The end plates are applied to the free end of a wall-mounted symmetric NACA 0012 airfoil and a cambered NACA 4412 airfoil with an aspect ratio of 2 and natural boundary layer transition. Microphone array measurements are taken in the aeroacoustic open-jet wind tunnel at BTU Cottbus-Senftenberg for chord-based Reynolds numbers between 75,000 and 225,000 and angles of attack from 0$$^\circ$$ ∘ to 30$$^\circ$$ ∘ . The obtained acoustic spectra show a broad frequency hump for the airfoil base configurations at higher angles of attack that is attributed to tip noise. Hot-wire measurements taken for one configuration show that the application of an end plate diffuses the vorticity at the tip. The aeroacoustic noise contribution of the tip can be reduced when the endplates are applied. This reduction is most effective for higher angles of attack, when the tip vortex is the dominant sound source. Graphic abstract

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