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A pitot–static system is a system of pressure-sensitive instruments that is most often used in aviation to determine an aircraft's airspeed, Mach number, altitude, and altitude trend. A pitot–static system generally consists of a pitot tube, a static port, and the pitot–static instruments. [1]
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A pitot-static system generally consists of a pitot tube, a static port, and the pitot-static instruments. [5] Errors in pitot-static system readings can be extremely dangerous as the information obtained from the pitot static system, such as airspeed, is potentially safety-critical. Several commercial airline incidents and accidents have been ...
It does this by giving an accurate measurement of the ambient atmospheric pressure (static pressure) well clear of the aircraft's fuselage. The trailing cone system trails at least one fuselage length behind the aircraft (SpaceAge Control) via a high-strength pressure tube. Static pressure is measured forward of the cone by several static ports.
An air data computer with inputs of pitot and static pressures is able to provide a Mach number and, if static temperature is known, true airspeed. [citation needed] Some authors in the field of compressible flows use the term dynamic pressure or compressible dynamic pressure instead of impact pressure. [3] [4]
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Pitot pressure is the pressure that is measured by a Pitot tube, an open-ended tube connected to a pressure-measuring device. For subsonic flow, pitot pressure is equal to the stagnation pressure (or total pressure) of the flow, and hence the term pitot pressure is often used interchangeably with these other terms.
Henri Pitot (French: [ɑ̃ʁi pito]; May 3, 1695 – December 27, 1771) was a French hydraulic engineer and the inventor of the pitot tube.. In a pitot tube, the height of the fluid column is proportional to the square of the velocity of the fluid at the depth of the inlet to the pitot tube.