History of NASA Icing Research Tunnel

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History of NASA Icing Research Tunnel ( history-nasa-icing-research-tunnel )

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The IRT Takes Shape Figure 2–8. Aerial view of the Flight Propulsion Research Laboratory, Cleveland, Ohio, 1946. (NACA C-15680) accomplished by passing heated gases through passages within the component walls, by internal or external electrical heating pads, or by electrical eddy currents induced by a pul- sating magnetic field in the elements to be protected. The hot-gas bleedback system operated by injecting hot gas into the air stream at the inlet, which protected the engine and most com- ponents in the inlet duct from icing. Finally, inertia separation of super-cooled water droplets out of the engine inlet air stream would be accomplished by a special inlet and duct design. Using scaled mockups of the engine inlet components, the researchers tested the effectiveness of various ice-protection methods in simulated icing conditions with tem- peratures as low as -30°F and airspeeds up to 300 miles per hour. Measuring cloud droplet size and liquid water content in the tunnel by the rotating cylinder method, they were satisfied that the simulated cloud was “in the range” of natural icing conditions. 35

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