Abstract: A static pressure measurement probe system comprises: a base to be fixed onto the cockpit of an aircraft; at least one local pressure tapping formed through the base and coupled to a pressure measurement sensor; for each local pressure tapping, at least two assemblies each comprising an optical window that is transparent to a laser radiation and a laser anemometry probe configured to take anemometry measurements in an imaginary cylinder centred on the local pressure tapping and of a diameter less than 3 cm and of a height less than 4 cm counted from the outer end of the local pressure tapping, so that the measurements are within the airflow limit layer.