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Types of pitot tubes A pitot-static tube connected to a manometer Pitot tube on Kamov Ka-26 helicopter A Formula One car during testing with frames holding many pitot tubes Location of pitot tubes on a Boeing 777. A pitot tube (/ ˈ p iː t oʊ / PEE-toh; also pitot probe) measures fluid flow velocity.
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 ...
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.
where is the density of the fluid, is the (slower) fluid velocity where the pipe is wider, and is the (faster) fluid velocity where the pipe is narrower (as seen in the figure). The static pressure at each position is measured using a small tube either outside and ending at the wall or into the pipe where the small tube is perpendicular to the ...
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 Bernoulli equation applicable to incompressible flow shows that the stagnation pressure is equal to the dynamic pressure and static pressure combined. [ 1 ] : § 3.5 In compressible flows , stagnation pressure is also equal to total pressure as well, provided that the fluid entering the stagnation point is brought to rest isentropically .
The formula to compute Mach number in a supersonic compressible flow can be found from the Rayleigh supersonic pitot equation (above) using parameters for air: M ≈ 0.88128485 ( q c p + 1 ) ( 1 − 1 7 M 2 ) 2.5 {\displaystyle \mathrm {M} \approx 0.88128485{\sqrt {\left({\frac {q_{c}}{p}}+1\right)\left(1-{\frac {1}{7\,\mathrm {M} ^{2}}}\right ...