Investigation of wing installation effects on the sound field of a model jet engine

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Chapter4. DataAnalysis 46 4.2 Flight Stream Effect This Section presents tests where only the flight stream was present. Though two simulations have been run at 70 ms−1 (DLR 247) and 90 ms−1 (DLR 248) FS veloc- ities, representing approach and cutback/sideline conditions respectively, only plots of the latter will be shown here, as the sound fields do not differ substan- tially, with DLR 248 averaging at an 8 dB higher SPL maximum than DLR 247 over all analysed frequencies. Figure 4.4 shows a low- and high-frequency TOB plot of DLR 248. (a) TOB 1000 Hz (b) TOB 4000 Hz Figure 4.4: SODIX plots of a testpoint with flight stream simulation only (DLR 248), using the developed source position grid (Fig. 3.12). The main source event is localized by SODIX at the leftmost grid position. Judg- ing by the symmetric moiré-like patterns occuring over all frequencies, SODIX seems unable to detect true sources within the given source position grid. As the algorithm needs to distribute sound energy to specific sources, it tries to place those at the most likely positions in the provided field. The flight stream noise does not perturbate into the measurement area, otherwise the entire plot would be of the same intensity. It is likely that the flight stream noise is caused by tur- bulent flows due to potential core collapsing or by surface interaction along the test rig. According to the QQ test report, the extra large fan supplying the flight stream air should not be the source of this sound, as it is intergrated into an ex- tensive silencing arrangement [37]. Figure 4.5 shows the spectrum plots of DLR 248 (sideline FS), DLR 317 (jet sideline without FS) and DLR 325 (jet sideline with FS), see also Sect. 4.3.1 and 4.3.2.

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