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TRANSONIC FAN FOR AIRCRAFT AIR-CONDITIONING UNIT.
NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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This study presents the results of the aerodynamic design of a transonic axial-flow fan for an aircraft air-conditioning unit. The design is based on fan design-point specifications and the experimental test results for a model of a proposed fan-inlet. The fan-inlet model was tested under flow conditions that gave Reynolds number similarity to the design inlet conditions. Three-dimensional pressure probes were used to measure the model discharge flow conditions at eight stations. It was necessary to circumferentially average the velocity distribution and mass-average the total-pressure loss in order to provide a basis for the fan design. Concurrently another design based on uniform flow and model losses was made. The results were nearly identical. Author
APPROVED FOR PUBLIC RELEASE