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An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic att

An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic attenuating section.

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1. An acoustic-attenuating wall panel, comprising: a radiused portion of an inner wall panel of a nacelle;the radiused portion including an airflow surface having a concave configuration being exposed to an airflow; andthe radiused portion comprising an acoustic attenuating section and formed as a h

1. An acoustic-attenuating wall panel, comprising: a radiused portion of an inner wall panel of a nacelle;the radiused portion including an airflow surface having a concave configuration being exposed to an airflow; andthe radiused portion comprising an acoustic attenuating section and formed as a honeycomb sandwich structure having a honeycomb core sandwiched between a pair of face sheets;the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel: a barrel portion, an upper bifurcation, a lower bifurcation. 2. The acoustic-attenuating wall panel of claim 1 wherein: the honeycomb sandwich structure is a metallic honeycomb sandwich structure. 3. The acoustic-attenuating wall panel of claim 1 wherein: the honeycomb core has a core thickness; andthe airflow surface is provided by an airflow face sheet having an inner radius; andthe inner radius being formed at an inner radius/core thickness ratio of no less than approximately 2:1. 4. The acoustic-attenuating wall panel of claim 3 wherein: the inner radius is no less than approximately 2.0 inches. 5. An inner wall panel, comprising: a semi-circular barrel portion having circumferentially opposite ends;an upper bifurcation wall portion and a lower bifurcation wall portion extending radially outwardly from the circumferentially opposite ends of the barrel portion;an upper radiused portion and a lower radiused portion joining the respective upper and lower bifurcation wall portion to the circumferentially opposite ends of the barrel portion; andat least one of the upper and lower radiused portions being formed as a honeycomb sandwich structure having a honeycomb core sandwiched between a pair of face sheets, the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel: a barrel portion, an upper bifurcation, a lower bifurcation; andthe inner wall panel comprising a metallic, one-piece, unitary structure. 6. The inner wall panel of claim 5 wherein: the inner wall panel forms part of a nacelle of a gas turbine engine. 7. The inner wall panel of claim 5 wherein: the upper and lower radiused portion each include an airflow surface having a concave configuration being exposed to an airflow through a nacelle. 8. The inner wall panel of claim 5 wherein: at least one of the upper and lower radiused portions comprises an acoustic attenuating section. 9. The inner wall panel of claim 5 wherein: both of the upper and lower radiused portions comprise a honeycomb sandwich structure. 10. An aircraft, comprising: a nacelle connected to a turbine engine, the nacelle having an inner wall panel positioned along a duct airflow path of an airflow;the inner wall panel having a radiused portion including an airflow surface having a concave configuration being exposed to an airflow;the radiused portion comprising an acoustic attenuating section and formed as a honeycomb sandwich structure having a core sandwiched between a pair of face sheets; andthe honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel: a barrel portion, an upper bifurcation, a lower bifurcation. 11. The aircraft of claim 10 wherein: the the honeycomb sandwich structure is a metallic honeycomb sandwich structure. 12. The aircraft of claim 10 wherein: at least one of the face sheets comprises an airflow face sheet forming an airflow surface exposed to the airflow; andat least a portion of the airflow face sheet having a plurality of holes fluidly coupling the cells to the airflow. 13. The aircraft of claim 11 wherein: the honeycomb core has a core thickness;the airflow surface is provided by an airflow face sheet having an inner radius; andthe inner radius being formed at an inner radius/core thickness ratio of no less than approximately 2:1. 14. The aircraft of claim 13 wherein: the inner radius is no less than approximately 2.0 inches. 15. The aircraft of claim 11 wherein: the nacelle includes a bifurcated fan duct defined by the inner wall panel and an outer wall, the inner wall panel extending between generally radially opposite sides of the outer wall;the inner wall panel comprising a semi-circular barrel portion having an upper bifurcation wall portion and a lower bifurcation wall portion extending radially outwardly from circumferentially opposite ends of the barrel portion;each one of the upper and lower bifurcation wall portions being joined to the barrel portion by a respective upper and lower radiused portion; andthe inner wall panel being formed as a one-piece, unitary structure. 16. A method of attenuating noise of a turbine engine, comprising the steps of: passing an airflow along a concave airflow surface of a radiused portion of an inner wall panel within a nacelle, the radiused portion comprising a honeycomb sandwich structure including a honeycomb core sandwiched between a pair of face sheets and having a plurality of cells, the honeycomb core in the radiused portion has a cell width that is the same as the cell width of the honeycomb core in at least one of the following portions of the inner wall panel: a barrel portion, an upper bifurcation, a lower bifurcation;fluidly coupling the cells to the airflow through a plurality of holes formed in an airflow face sheet of the honeycomb sandwich structure; andabsorbing acoustic energy in the airflow fluidly coupled to the cells. 17. The method of claim 16 further comprising the steps of: passing a portion of the airflow through the holes such that the airflow enters the cells; andabsorbing acoustic energy in response to the airflow entering the cells. 18. The method of claim 16 wherein: the honeycomb sandwich structure is a metallic honeycomb sandwich structure. 19. The method of claim 16 wherein the airflow face sheet has an inner radius, the honeycomb core having a core thickness, the method further comprising the step of: providing the airflow face sheet with an inner radius having an inner radius/core thickness ratio of no less than approximately 2:1. 20. The method of claim 16 further comprising the step of: providing the airflow face sheet with an inner radius at no less than approximately 2.0 inches.