ICE ACCRETION SIMULATION AND SCALING ANALYSIS FOR CONCEPTUAL DESIGN OF AN ICING WIND TUNNEL

Date

2023-8-08

Author

Özkanaktı, Mehmet Harun

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Icing in aerodynamic structures is one of the most important problems to be considered due to its negative impact on the performance of aerodynamic components and its potential to cause fatal accidents. Hence, it is necessary to conduct experimental studies to investigate the causes, intensity, and physics of icing. Additionally, certification processes and compliance with these processes are inevitable in the development of aircraft. For these reasons, icing wind tunnel (IWT) studies are the most suitable method in terms of cost, safety, and feasibility for icing prediction and certification. However, since the dimensions of these components are often large for existing IWTs, it is necessary to conduct a scaling study to directly obtain in-flight icing. In this study, a similitude model was developed that matches the geometry, flow-field, droplet trajectory, total water catch, energy balance, and surface-water dynamics. Based on the terms in this similitude model, a scaling calculation was performed using the Modified Ruff Method due to its superior accuracy and inclusion of more scaling terms. The outputs of these calculations were used to analyze different reference conditions using the Aeromsice-2D icing prediction code, and the experimental data was compared with the reference and scaled icing results. The technical specifications of the icing wind tunnel were determined based on the limitations and physical requirements of these calculations and the requirements specified in 14 CFR Appendix C to Part 25. Various scenarios consisting of different air velocity, droplet sizes, temperatures, and ice accumulation conditions, as well as the technical information and limitations obtained from the scaling, were used to perform the conceptual design of an IWT and its verification was carried out using the commercial computational fluid dynamics software ANSYS Fluent. The design process was revised based on the results obtained and the IWT design reached its final form.

Subject Keywords

In-flight Icing, Icing Scaling, Icing Similitude, Ice Accretion, Experimental Aerodynamics, Icing Wind Tunnel

URI

https://hdl.handle.net/11511/105221

Collections

Graduate School of Natural and Applied Sciences, Thesis