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A pitot tube (/ ˈ p iː t oʊ / PEE-toh; also pitot probe) measures fluid flow velocity. It was invented by French engineer Henri Pitot in the early 18th century, [ 1 ] and modified to its modern form in the mid-19th century by Henry Darcy . [ 2 ]
Examples of pitot tube, static tube, and pitot–static tube Static ports fitted to an Airbus A330 passenger airliner. The pitot–static system of instruments uses the principle of air pressure gradient. It works by measuring pressures or pressure differences and using these values to assess the speed and altitude. [1]
A pitot tube is used to measure fluid flow velocity. The tube is pointed into the flow and the difference between the stagnation pressure at the tip of the probe and the static pressure at its side is measured, yielding the dynamic pressure from which the fluid velocity is calculated using Bernoulli's equation. A volumetric rate of flow may be ...
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. This relationship was discovered by Henri Pitot in ...
Indicated airspeed measured by pitot-tube can be approximately expressed by the following equation delivered from Bernoulli's equation. () NOTE: The above equation applies only to conditions that can be treated as incompressible. Liquids are treated as incompressible under almost all conditions.
u is the local flow velocity with respect to the boundaries (either internal, such as an object immersed in the flow, or external, like a channel), and; c is the speed of sound in the medium, which in air varies with the square root of the thermodynamic temperature. By definition, at Mach 1, the local flow velocity u is
Aircraft have pitot tubes for measuring airspeed. In aviation, airspeed is the speed of an aircraft relative to the air it is flying through (which itself is usually moving relative to the ground due to wind). It is difficult to measure the exact airspeed of the aircraft (true airspeed), but other measures of airspeed, such as indicated ...
The two points of interest are 1) in the freestream flow at relative speed where the pressure is called the "static" pressure, (for example well away from an airplane moving at speed ); and 2) at a "stagnation" point where the fluid is at rest with respect to the measuring apparatus (for example at the end of a pitot tube in an airplane).