CPC F02C 7/32 (2013.01) [F05D 2220/323 (2013.01)] | 15 Claims |
1. An aircraft engine, comprising:
an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine to an outlet within the aircraft engine; and
at least one strut having a leading edge and a trailing edge and extending across at least part of the air inlet duct, the at least one strut having a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage via a plurality of measurement tap passages, the strut passage having a radially innermost point positioned at a radially outermost point of a radially innermost measurement tap passage of the plurality of measurement tap passages.
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