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Chapter4. DataAnalysis 50 Table 4.1: Test points simulating ICAO reference measurement. All tests were carried out on a baseline short-cowl engine without additional sound excitation. DLR TP 317 435 279 411 287 395 325 443 257 423 297 403 Condition Flight Stream Wing SL No No SL No Yes CB No No CB No Yes APP No No APP No Yes SL Yes No SL Yes Yes CB Yes No CB Yes Yes APP Yes No APP Yes Yes Sideline ICAO reference point without wing installation The SODIX plots of TP DLR 317 are shown in Fig. 4.8 for four different TOB, giving an overview of the SPL and source directivity trends with increasing fre- quency. For the 250 Hz TOB, the maximum SPL is approximately 94 dB and is located at x/d ≈ 7, where the main low-frequency mixing takes place. The radiation shows a clear rearward component. The plot suggests that the true sound maximum of the jet radiates even further downstream and is subsequently outside of the angular range. This observation carries through most of the analysed tests. For future tests it is therefore suggested to extend the linear microphone array further downstream in order to pick up signals at lower emission angles (θ = 30◦ . . . 50◦). As expected, the SPL maximum moves upstream with increasing frequency. At a frequency of 1250 Hz, the absolute SPL maximum is reached, which equals St = 1 at x/d = 5. This behaviour is consistent with the theory presented in Sect. 2.3.3. As the frequency increases further, the SPL maximum of each TOB decreases and moves closer to the nozzle outlet plane. This connection can be ascribed to the fact, that high frequency noise is caused by small eddies, which mainly occur in the primary mixing zone of the jet. With increasing jet length, the eddies widen, causing the frequency of their generated noise to become lower.PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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