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Chapter4. DataAnalysis 59 Figure 4.14: Sound wave refraction caused by the flight stream, TOB 5000 Hz of DLR 325 and DLR 317. The FS displaces sources by ≈ 0.5x/d. The sound directivity characteristics of the plots of DLR 325 in Fig. 4.12 are similar to those of the uninstalled testing case. There appears to be a general rearward directivity for low frequencies. Again, it can not be ruled out that the true noise source is further downstream and therefore outside the angular range of the plot. Installed sideline ICAO reference point with flight stream The wing effect comparison directivity plots for sideline conditions with FS are shown in Fig. 4.15. The plots show no large differences to the experiments without FS (Fig. 4.9). Again, the addition of flight stream simulation moves sound events downstream due to refraction effects. This happens irrespective of whether a wing is installed or not. However, the absolute SPL difference between TPs with and without flight stream is noticable. Whereas wing installation results in an up to 10 dB in- crease in sound intensity without FS simulation, the experiments with FS exhibit an up to 20 dB SPL increase compared to no FS, being greater for intermediate TOBs. As the wing is fully engulfed by the flight stream, the additional noise difference most likely results from flow interaction with the wing surface. It has to be noted that the flight stream only increases the relative difference between installed and isolated test cases, but has an overall reduction effect on the SPL as explained above. The directivity of the sound events is similar between both configurations as well, though the plots appear to be more blurry when the flight stream is enabled. Besides this, there are the same additional sources: One at the nozzle outlet radiating to the front microphones and one encompassing the wing and radiating mainly downstream. The area with reduced sound pressure just behind the wing at TOB 1250 Hz is also present and even more pronounced.PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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