von Glahn, Uwe., Blatz, Robert E.
Aerodynamic and icing investigations of several internal water-inertia-separation inlets designed to prevent entrance of water into a turbojet engine in an icing condition are presented. Comparisons of total-pressure loss, mass flow, and icing characteristics are made. Complete icing protection of inlet guide vanes was not achieved. Approximately 8 percent of the volume of water entering the inlets remained in the air. For non-icing operation, total-pressure losses were comparable to those of direct-ram inlets. Under icing conditions, considerable total-pressure losses were obtained with inertia-separation inlets.
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