Systems and methods for variable alignment aerodynamic probes

A gas turbine engine comprising:

• a fan section having a fan case;
• a compressor section having a compressor case;
• a turbine section having a turbine case;
• and
• a variable alignment aerodynamic probe comprising:
• a probe body having a leading edge and extending radially into a vane case;
• a sensor element proximate the leading edge;
• and
• a bearing coupled to the probe body and the vane case;
• wherein the probe body is configured to rotate in response to a turned flow within the vane case,
• wherein the rotation of the probe body is configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°.

An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising:

• receiving, by the processor, a first data from a first sensor and a second data from a second sensor;
• determining, by the processor, a first angle of attack difference based on the first data and the second data;
• calculating, by the processor, a first angle of attack response based on the angle of attack difference, wherein the angle of attack response is configured to null the angle of attack difference;
• and
• controlling, by the processor, a first servomotor and, in response, rotating a probe body about a first axis.