Control of flow separation by sound

Ahuja, K. K.; Burrin, R. H.

doi:10.2514/6.1984-2298

Cited by 104 publications

(40 citation statements)

References 2 publications

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“…The two-stream centerline velocity decay data are shown in figure 6 in terms of equation (2). It is apparent that the Le term provides good correlation of the excited and unexcited centerline two-stream velocity decay data.…”

Section: Centerline Velocity Decaymentioning

confidence: 93%

Preliminary analysis of tone-excited two-stream jet velocity decay

Glahn

1985

The Journal of the Acoustical Society of America

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Acoustic research related to jet flows has established that sound, by amplifying the naturally occurring large-scale structures in turbulent shear layers, can cause a more rapid decay of the jet plume velocity and temperature and jet spread. One possible application of this sound-flow interaction phenomenon is to future STOL aircraft that may require modified jet plume characteristics in order to reduce the loads and temperatures on the deflected flaps during takeoff and landing operations. A preliminary analysis is made herein of the tone-excitation effect on the velocity decay of model-scale, two-stream jet plumes. Measured data are correlated in terms of parameters that include excitation sound level and outer-to-inner steam velocity ratio. The effect of plume tone-excitation on farfield jet noise is examined briefly and its implication for large-scale two-stream jets is discussed.

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Section: Centerline Velocity Decaymentioning

confidence: 93%

Preliminary analysis of tone-excited two-stream jet velocity decay

Glahn

1985

The Journal of the Acoustical Society of America

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“…The higher vorticity flux levels suggest that a somewhat improved performance can be expected from the SAP airfoil. 4. CONCLUDING REMARKS Success in controlling compressible dynamic stall using a dynamically shape adaptive airfoil (as determined by the peak suction pressure development, vorticity flux and deformation schedule) has been reported.…”

Section: E Vorticity Flux Distributionsmentioning

confidence: 99%

Compressible dynamic stall control using a shape adaptive airfoil

Chandrasekhara

Wilder²,

Carr

1999

37th Aerospace Sciences Meeting and Exhibit

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“…Acoustic excitation 10 has also been used to control unsteady separated ows, but the acoustic power requirements increase disproportionately with increasing Mach number, and, thus, it does not appear to be practical for compressible dynamic stall control.…”

Section: Nomenclaturementioning

confidence: 99%

Compressible Dynamic Stall Control: Comparison of Two Approaches

Chandrasekhara

Wilder

Carr

2001

Journal of Aircraft

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The approaches of compressible dynamic stall control using real-time airfoil adaptation and slatted airfoils are compared. Each method attempts to solve the unsteady ow separation and the underlying causes differently. The approaches lead to unexpected results: For the slatted airfoil, dynamic stall alleviation on the main airfoil with a fully stalled slat occurred, and for the shape adapting airfoil, leading-edge attached ow with trailing-edge separation was obtained. In both cases, no dynamic stall vortex was present. As can be expected, the control effectiveness of each method varies over the full cycle and depends on the Mach number due to the new factors introduced by the use of the methods. These issues are addressed. Nomenclature

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Control of flow separation by sound

Cited by 104 publications

References 2 publications

Preliminary analysis of tone-excited two-stream jet velocity decay

Preliminary analysis of tone-excited two-stream jet velocity decay

Compressible dynamic stall control using a shape adaptive airfoil

Compressible Dynamic Stall Control: Comparison of Two Approaches

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