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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 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).
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.
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. For supersonic flow, however, pitot pressure is the stagnation pressure of the flow behind the normal shock ahead of the pitot tube.
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.