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accuracy. The numberof shapefuncti<strong>on</strong>sJ is chosensufficiently large to captureat Ieast 2-3 t_mes the<br />

number of oscillati<strong>on</strong>s in _ expected al<strong>on</strong>g the duct; this number can be inferred from the incident field<br />

given in eq. (6).<br />

RESULTS<br />

Numerical predicti<strong>on</strong>s from the theory outlined in thispaper are illustrated in figs. 2 and 3.<br />

Figure 2 corresp<strong>on</strong>ds to the case of primary interest in the current proceedings: the forward Mach<br />

number is 0.5, the duct (D) diameter and length are both I m, and the dimensi<strong>on</strong>less clrcular frequency<br />

is tzD/c=16r_. On the figure is shown the sound pressure level in dB re lO-51.tPa radiated from a<br />

m<strong>on</strong>opole for which pc tAI= IN. The polar plot gives the SPL of the incident field al<strong>on</strong>e and that of the<br />

total field in the presence of the duct <strong>on</strong> a spherical radius 2.5m from the origin of _. The angles 0 °<br />

and 180 ° corresp<strong>on</strong>d to the exit and inlet ends of the duct, respectively. As would be expected at this<br />

relatively high frequency, the duct causes very little scattering in the axial directi<strong>on</strong>s. There is, however,<br />

a lateral shielding effect that cuts the SPL about 20dB around the 90 ° directi<strong>on</strong> as is seen in all<br />

problems of this type [1, 2, 7].<br />

Figure 3 illustrates the directivity found for the same case except with the frequency reduced to<br />

wD/c=4.409n (corresp<strong>on</strong>ding to 750 Hz). While the axial scattering is somewhat str<strong>on</strong>ger in this case,<br />

the duct obviously affords minimal lateral shielding at the lower frequency.<br />

ACKNOWLEDGMENTS<br />

This research was supported by NASA Langley Research Center under Cooperative Agreement<br />

NCCI-14. Essential assistance with computer code development was provided by Mr. Melvin<br />

Kosanchick III, Ms. Barbara Lakota and Mr. Jas<strong>on</strong> Buhler.<br />

.<br />

.<br />

.<br />

REFERENCES<br />

Myers, M. K. and Lan, J. H., "Sound Radiati<strong>on</strong> from Ducted Rotating Sources in Uniform Moti<strong>on</strong>."<br />

AIAA Paper No. 93-4429, October 1993.<br />

Myers, M. K., "Boundary Integral Formulati<strong>on</strong>s for Ducted Fan Radiati<strong>on</strong> Calculati<strong>on</strong>s."<br />

Proceedings of First Joint CEAS/AIAA Aerocoustics C<strong>on</strong>ference, Munich, Germany, Vol. I, June<br />

1995, pp. 565-573.<br />

Eversman, W., "Ducted Fan Acoustic Radiati<strong>on</strong> Including the Effects of N<strong>on</strong>uniform Mean Flow and<br />

Acoustic Treatment." AIAA Paper No. 93-4424, October 1993.<br />

24<br />

i

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