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The blockage of all of the static ports is one of the few common-failure modes resulting in total failure of multiple basic flight instruments and, as such, is regarded as one of the most serious faults that can occur in avionics systems. [12] The design of the aircraft did not incorporate a system of maintenance covers for the static ports.
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. [1] A pitot–static system generally consists of a pitot tube, a static port, and the pitot–static instruments. [2]
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. [3] The cone stabilizes and aligns the ports relative to the freestream airflow. [4]
To do this, one makes use of the fact that above the speed for best glide the polar sink speed of the sailplane increases roughly with the square of the airspeed. Since the pitot pressure also increases with the square of the speed, one can use it to 'compensate away' the effect of sailplane polar sink over virtually the entire speed range."
[1]: 8–10 [3] [4] The pitot tube may become blocked, because of insects, dirt or failure to remove the pitot cover. A blockage will prevent ram air from entering the system. If the pitot opening is blocked, but the drain hole is open, the system pressure will drop to ambient pressure, and the ASI pointer will drop to a zero reading. If both ...
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]
X-15 rocket-powered research aircraft, with nose air data boom. An air data boom provides air pressure, temperature, and airflow direction data to data acquisition systems for the computation of air, ground, and water vehicle orientation, speed, altitude/depth, and related information.
The air pressure in the vicinity of the static port is conveyed by a conduit to the altimeter and the airspeed indicator. This static port and the conduit constitute the aircraft's static system. The objective of the static system is to sense the pressure of the air at the altitude at which the aircraft is flying.