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Chapter4. DataAnalysis 65 Sideline Conditions with Flight Stream Sideline conditions were chosen to investigate the influence of broadband noise with enabled jet flow over approach and cutback conditions. Figure 4.20 shows the plots for TPs DLR 350 and 444, with the standard 20 dB dynamic range. There is one malfunctioning microphone in Fig. 4.20(a) showing as a dark blue line. (a) Isolated, DLR 350 (b) Installed, DLR 444 Figure 4.20: Broadband noise excitation with sideline flow conditions and flight stream enabled, TOB 2000 Hz. The absolute SPL maximum is higher compared to the no flow case presented before, which is to be expected, considering the turbulent mixing noise caused by the core mass flow. In addition, the sound source distribution is concentrated in a smaller area, meaning that the mixing sources that usually occur further down- stream of the nozzle are less significant than the simulated broadband noise. The directivity of the source field is similar to the no flow case described above, being relatively uniform with the strongest sources close to the nozzle. The presence of the flight and core streams causes the main sound source to appear more diluted, as the sound waves are refracted in the shear layer of the jet. The wing presence causes the maximum SPL to rise by approximately 3 dB, which is significantly lower compared to previously assessed TPs with similar conditions but without broadband sound excitation (DLR 325 and 443). There is a new source at the wing tip with forward directivity that is about 10 dB below the main sound source. In addition, the directivity of the main source changes slightly; it moves further to the flap and has a more pronounced rearward emission. It is notable, that this time an area of very low SPL occurs when the wing is present, Fig. 4.21. This gives further credence to the assumption that this area results from the SODIX calculation in conjunction with the experiment setup and is not an actual physi- cal phenomenon.PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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