Document Type

Honors Thesis


The technological necessities of the modern helicopter are always evolving. However, helicopters themselves are rarely modified to compensate for these new technologies. Because of this, as more precise electrical equipment replaces archaic analog instruments, unexpected issues arise in these older vehicles that were not present before. Temperatures within the helicopter cabin and control panel reach dangerous levels, causing extreme discomfort for the pilot as well as causing equipment failure. To amend this issue, cooling methods must be employed to prevent failure of instrumentation which will also reduce temperatures in the cabin. The primary goal of the project is to create a cooling method that provides the most cooling to the control panel. This report summarizes the computational fluid dynamic simulation results completed and analyzed by the Honors Student, which include various cooling methods that will be reported to Airbus.

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