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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. [5]
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]
The pitot tube supplies pressure to the airspeed indicator. Pitot pressure is equal to stagnation pressure providing the pitot tube is aligned with the local airflow, it is located outside the boundary layer, and outside the wash from the propeller.
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).
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.
The measurement and indication of airspeed is ordinarily accomplished on board an aircraft by an airspeed indicator (ASI) connected to a pitot-static system. The pitot-static system comprises one or more pitot probes (or tubes) facing the on-coming air flow to measure pitot pressure (also called stagnation, total or ram pressure) and one or ...
Pitot intake operating modes. Pitot inlets are used for subsonic aircraft. A pitot inlet is little more than a tube with an aerodynamic fairing around it. When an aircraft is not moving, and there is no wind, air approaches the intake from all directions: directly ahead, from the side, and from behind.
They commonly have the pitot and static pressure inputs, as well as outside air temperature from a platinum resistance thermometer and may control heating of the pitot tube and static vent to prevent blockage due to ice. On simpler aircraft, there is usually not a fly-by-wire system so the outputs are typically to the cockpit altimeters or ...