The European Union (EU) ‘Clean Sky’ [1] Joint Technology Initiative (JTI) is a research programme aimed at developing breakthrough technologies which will minimise the impact of aviation on the environment. Within this, the System for Green Operations (SGO) Integrated Technology Demonstrator (ITD) looks to improve aircraft operation through management of energy and mission trajectory.
As part of the SGO ITD, a series of environmental icing tests have been conducted on an ice protected, acoustically protected, electrically powered, scoop intake and channel. The range of conditions tested included in-flight icing (CS-25 Appendix C, same as 14 CFR 25), super-cooled large droplets (proposed 14 CFR 25 Appendix O, [2]), snow and ice crystal conditions as well as ground icing in freezing fog conditions.
This paper describes the analysis undertaken to design the ice protection system (IPS) for the scoop and channel, including the challenges faced with this geometry, the tools employed, and the general design guidelines. The paper also describes the analysis undertaken to ensure that the test conditions achievable in the icing wind tunnel are representative of the in-flight icing conditions. A brief summary of the outcome of the environmental icing tests is also provided, although this is not the main subject of the current paper.