Computation of aircraft airspeed by inclusion of static air temperature

A system comprising:

• a static air temperature probe attached to an aircraft, wherein the static air temperature probe is mounted on a fuselage of the aircraft at a location where a computational fluid dynamics analysis indicates that an air temperature proximate to the fuselage is substantially equal to an outside air temperature;
• flight control electronics;
• and
• a processor configured to:
• measure a static air temperature at the aircraft using the static air temperature probe;
• calculate a Mach number associated with the aircraft based at least partially on the static air temperature;
• calculate a true air speed of the aircraft based at least partially on the Mach number;
• and
• operate, via the flight control electronics, the aircraft using the true air speed.

A system comprising:

• an aircraft;
• a static air temperature probe configured to measure a static air temperature at the aircraft, wherein the static air temperature probe is mounted on a fuselage of the aircraft at a location where a computational fluid dynamics analysis indicates that an air temperature proximate to the fuselage is substantially equal to an outside air temperature;
• one or more processors configured to calculate a true air speed based at least in part on the static air temperature;
• and
• flight control electronics configured to operate the aircraft using the true air speed.