An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel within which hot air flows and a panel for acoustic treatment having, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and a reflective layer as well as ducts for channeling hot air, each including one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises at least a stabilization chamber in the form of an annular channel with a cross-section larger than that of the ducts which extends over at least a portion of the nacelle circumference and which communicates with a plurality of ducts, the inlets and outlets not being aligned in the longitudinal direction.