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Chapter5. ConclusionandOutlook 77 amount. Both effects cancelled each other out in most test cases, resulting in a sound field comparable to isolated testing. When compared to the baseline short cowl configuration, the sound reduction effects of the serrated nozzle design as well as long cowl configuration were confirmed using source directivity analysis, both reducing the average SPL of the sound field by 3 dB. The wing presence lead to interesting behaviour, partly nullifying the benefit. The scarfed nozzle design only showed a minor interaction noise reduction effect when a wing was present, but did not change the mixing noise noticeably. Generally, tests using wing in- stallation and flight stream simulation should be carried out preferably, provided that the testing budget permits this, as they facilitate a more holistic approach to sound field analysis and reflect the conditions during real flight better than the stationary isolated tests carried out in the course of aeroengine noise certification. All in all, the findings of this thesis correspond well with the elaborated theory. The source directivity analysis proved a valuable tool in assessing the ramifi- cations of wing and flight stream presence. The plots revealed a much greater significance of both aspects then expected. Universally valid conclusions cannot be drawn from the data, however, considering the statistically low amount of test points investigated. Based on the results obtained in the scope of this thesis, recommendations on future test setup were given. This especially concerns the layout of the linear microphone array, which was found to be of insufficient length and have too high spacing between microphones. As a next working step, the obtained data should be projected to the farfield and comparisons with the QinetiQ farfield data from the OPENAIR experiment should be made. Additionally, further research of the sound field of a scarfed nozzle with a wing installed could potentially yield interesting results.PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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