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A NACA duct, [1] also sometimes called a NACA scoop or NACA inlet, is a common form of low-drag air inlet design, originally developed by the U.S. National Advisory Committee for Aeronautics (NACA), the precursor to NASA, in 1945.
These were speeds Lockheed engineers considered useless for their purposes. General Henry H. Arnold took up the matter and overruled NACA objections to higher air speeds. NACA built a handful of new high-speed wind tunnels, and Mach 0.75 (570 mph (495 kn; 917 km/h)) was reached at Moffett's 16-foot (4.9 m) wind tunnel late in 1942. [10] [11]
The original intake is shown in the top image. The fundamental design of a gas turbine engine is such that the air flow-rate entering its compressor is regulated by the amount of fuel burned in its combustor. For supersonic flight the air entering the inlet also has to be regulated to a similar amount by the design of the entrance of the inlet ...
P-51 radiator duct schematic diagram: 1 - air duct flap control system, 2 - air intake, 3 - oil radiator, 4 - oil radiator air exhaust, 5 - engine coolant radiator, 6 - air duct flaps, 7 - main air exhaust. The duct must be travelling at a significant speed with respect to the air for the effect to occur. Air flowing into the duct meets drag ...
Air bled from the engine fan is blown across the pre-cooler, located in the engine strut, and absorbs excess heat from the service bleed air. A fan air modulating valve (FAMV) varies the cooling airflow to control the final air temperature of the service bleed air. Notably, the Boeing 787 does not use bleed air to pressurize the cabin.
Aircraft using piston engines use intake systems similar to automobiles. With the development of jet engines and the subsequent ability of aircraft to travel at supersonic speeds, it was necessary to design inlets to provide the flow required by the engine over a wide operating envelope and to provide air with a high-pressure recovery and low distortion.