@inproceedings{,
    author = {Remiger, Jonas; Grois, Andreas; Stößel, Marcel; Kožulović, Dragan; Krummenauer, Michael },
    title = {Impact of Various Intake Configurations on the Flight Mission Performance of an Unmanned Aircraft},
    editor = {},
    booktitle = {Proceedings of the ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition, Volume 1: Aircraft Engine},
    series = {},
    journal = {},
    address = {},
    publisher = {ASME},
    edition = {},
    year = {2024},
    isbn = {978-0-7918-8792-9 },
    volume = {},
    number =  {},
    pages = {},
    url = {https://doi.org/10.1115/GT2024-122647},
    doi = {10.1115/GT2024-122647},
    keywords = {},
    abstract = {Well-defined intake-engine interfaces are of great importance in the aircraft design process. The focus of this paper is on various coefficients for data transfer at the aerodynamic interface plane (AIP) as a critical interface between the engine and the aircraft. To evaluate these coefficients, different intake geometries are modeled and simulated. The objective of the study is to provide a holistic view of the interactions between flight conditions, aircraft, intake systems and their effects on engine performance using previously generated computational fluid dynamics (CFD) results which are further used in the engine mission simulation system (EMSS). The effects of intake distortion on compressor behavior and engine performance are investigated using the parallel compressor model. All results of the investigation are obtained via the time-resolved simulation of an exemplary flight mission. The results first discuss the influence of flight conditions on the total pressure loss of each inlet and the corresponding behavior of the investigated distortion parameters. It is shown that not only the inlet geometry but also the coefficient used to represent the distortions in the performance calculation has an influence on the mission performance. Finally, it is shown that depending on the coefficient used to map the inlet distortion, there is a clear difference in the operating behavior of the compressor. The proposed γ coefficient predicts a critical approach to the surge margin. The DC60 would still suggest a safe operation of the compressor.},
    note = {},
    institution = {Universität der Bundeswehr München, Fakultät für Luft- und Raumfahrttechnik, LRT 12 - Institut für Strahlantriebe, Professur: Kožulović, Dragan},
    
    
}