The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterised in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.