@misc{KazulaHoeschler, author = {Kazula, Stefan and H{\"o}schler, Klaus}, title = {Ice detection and protection systems for circular variable nacelle inlet concepts}, series = {CEAS Aeronautical Journal}, volume = {11}, journal = {CEAS Aeronautical Journal}, number = {1}, issn = {1869-5590}, doi = {10.1007/s13272-019-00413-1}, pages = {229 -- 248}, abstract = {This paper presents the challenge of ice protection within a concept study for variable pitot inlets of aero engines in transonic and supersonic civil aviation. An overview of variable inlet concept groups that adjust the inlet geometry by rigid segment repositioning, elastic surface deformation, or boundary layer control is given. Ice detection mechanisms and various pneumatic, fluid, as well as electric ice protection systems are presented. These ice protection systems are assigned to the respective inlet concept groups and evaluated regarding economic, functional, and safety requirements by means of pairwise comparison and weighted point rating to determine the most suitable combinations.}, language = {en} } @misc{KazulaHoeschler, author = {Kazula, Stefan and H{\"o}schler, Klaus}, title = {Evaluation of variable pitot inlet concepts for transonic and supersonic civil aviation}, series = {Aircraft Engineering and Aerospace Technology}, volume = {92}, journal = {Aircraft Engineering and Aerospace Technology}, number = {6}, issn = {0002-2667}, doi = {10.1108/AEAT-11-2019-0225}, pages = {807 -- 815}, abstract = {Purpose - This paper aims to describe the selection of the ideal variable inlet concept group by using results of aerodynamic investigations, system safety analyses and integration studies. Design/methodology/approach - Aerodynamic and functional inlet requirements are explained and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. Findings - By means of this evaluation, the concept group that adjusts the inlet geometry by rigid segment repositioning is identified as most suitable concept group. Originality/value - The early selection of the most suitable concept group enables more detailed subsequent concept investigations, potentially enabling the technology of variable inlets for future commercial aircraft.}, language = {en} } @misc{KazulaWoellnerHoeschler, author = {Kazula, Stefan and W{\"o}llner, Mark and H{\"o}schler, Klaus}, title = {Identification of efficient geometries for variable pitot inlets for supersonic transport}, series = {Aircraft Engineering and Aerospace Technology}, volume = {92}, journal = {Aircraft Engineering and Aerospace Technology}, number = {7}, issn = {0002-2667}, doi = {10.1108/AEAT-11-2019-0228}, pages = {981 -- 992}, abstract = {Purpose - This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. Design/methodology/approach - The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. Findings - The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50\% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20\% for supersonic flight at Mach 1.6. Originality/value - Hence, the technology of circular variable pitot inlets for supersonic transport aircraft could be a way to achieve the ambitious ecological, safety and economic goals for future civil aviation.}, language = {en} } @misc{KazulaHoeschler, author = {Kazula, Stefan and H{\"o}schler, Klaus}, title = {Review of Variable Leading Edge Patents for Aircraft Wings and Engine Inlets and Their Relevance for Variable Pitot Inlets in Future Supersonic Transport}, series = {Deutscher Luft- und Raumfahrtkongress 2020, Online, 1. bis 3. September 2020}, journal = {Deutscher Luft- und Raumfahrtkongress 2020, Online, 1. bis 3. September 2020}, abstract = {The motivation for designing variable pitot inlets for future supersonic transport (SST) is explained. A comprehensive overview of existing technological solutions for variable leading edges of aircraft wings and engines inlets is given. The advantages and limitations of over 80 solutions, as well as their relevance for application on variable pitot inlets for SST are analysed. These analyses emphasis challenges of existing solution options concerning design methodologies, level of detail and experience with a technology.}, language = {en} } @misc{KazulaHoeschler, author = {Kazula, Stefan and H{\"o}schler, Klaus}, title = {A Variable Pitot-Inlet Concept for Supersonic Aviation}, series = {Global Power \& Propulsion Society GPPS Chania20, Online, 7th - 9th September 2020}, journal = {Global Power \& Propulsion Society GPPS Chania20, Online, 7th - 9th September 2020}, issn = {2504-4400}, doi = {10.33737/gpps20-tc-49}, pages = {10}, abstract = {An overview of aero-engine inlets, the design process in aviation and a safe design approach for academic studies is provided. By means of a safe design approach, a variable inlet concept is developed up to technology readiness level (TRL) 3 and described. The application of safety and reliability methods, aerodynamic and structural analyses, as well as functional demonstrators proves the feasibility of the present variable inlet concept and highlights its potential for application in future supersonic transport (SST).}, language = {en} }