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Chapter4. DataAnalysis 52 At 5 kHz, three distinct sound sources can be observed radiating into the forward arc, whereas SODIX locates the sources more uniformly for the downstream mi- crophones. This implies some form of wave interference in the forward quadrant which results in the trident shape. Beginning with the 5 kHz plot, the frequency response deviation of the microphones described in Sect. 3.2.1 can be seen. At 10 kHz, aliasing occurs, causing SODIX to falsely take away source energy from the main source and add it to the aliasing sources. In addition, the last two plots show clearly, that the source events start almost exactly at the nozzle outlet x = 0, as there is no source detected upstream of this plane. This implies that there are no significant noise sources on the aeroengine nacelle, but only in the free jet, which is to be expected without employing a simulated flight stream. Sideline ICAO reference point with wing installation Figure 4.9 shows the comparisons of installed (DLR 435) and isolated (DLR 317) jet. The uninstalled wing case is always subtracted from the installed case, so that positive values, represented in red, imply that the installed case is louder. The SPL difference between installed and isolated test configurations is generally about 12 dB, which is a rather significant increase. The aliasing effect becomes more prominent as well. In the low-frequency domain, additional sound sources occur primarily upstream of the nozzle and can most certainly be attributed to either sound wave reflection from the wing or surface/flow interactions. How- ever, as incidence and exit angles must correspond, the forward reflection would require an unusual negative incidence angle. Therefore, the physical validity of the 250 Hz plot is questionable. The high-frequency plots exhibit more expected behaviour. For the 1250 Hz TOB, there are two different areas with increased sound pressure, the first right at the nozzle radiating into the aft quadrant, the second in close proximity to the nozzle being picked up by almost the full linear array. At this frequency, the sources are most likely medium-scale eddies formed on the underside of the wing due to wall shear stress. These vortices only occur within a small frequency range; for higher frequencies the sources become more well-defined. On the latter two plots, there are two distinct noise sources. The first is on the same position as the one in the 1250 Hz plot, meaning that there is a turbulent event emitting a broadband noise that spans over all TOB. The second source travels further downstream with increasing frequency. As eddies tend to grow with increasing travel distance, thePDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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