Abstract: A turbofan engine includes: a core engine, a primary flow channel, a secondary flow channel, a machine axis and a thrust nozzle that is a separate thrust nozzle for the secondary flow channel or an integral thrust nozzle for the primary flow channel and the secondary flow channel, and that has a center line and a nozzle exit surface. The thrust nozzle is tilted with respect to the machine axis while forming an articulation angle that the center line of the thrust nozzle forms with respect to the machine axis at least at the nozzle exit, and the nozzle exit surface of the thrust nozzle is oriented obliquely with respect to the center line of the thrust nozzle while forming an angle of inclination that a normal of the nozzle exit surface forms with respect to the center line of the thrust nozzle.

Abstract: An enclosed test stand may be enclosed by at least two reverberant boundary surfaces. Two of said at least two reverberant boundary surfaces may abut against each other to form an edge. A first linear array of microphones may be configured to detect acoustical signals of a sound field. The linear array of microphones may be arranged along the edge. An evaluating unit may be coupled to the linear array of microphones. The evaluating unit may be configured to locate sound sources of the sound field.