Aerodynamically shaped static pressure sensing probe

Measuring and testing – Fluid flow direction – Relative to aircraft or watercraft

Reexamination Certificate

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Reexamination Certificate

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06915687

ABSTRACT:
A static pressure sensing probe has an aerodynamically shaped cross section, and extends laterally from an aircraft surface sufficiently so that an outer end of the probe is a short distance outside the boundary layer on the aircraft surface on which the probe is mounted. The probe has surface corrugations or ridges along the probe, and the ridges include an upstream ridge adjacent the leading edge, and a downstream ridge spaced rearwardly from the upstream ridge. The ridges cause pressure disturbances along the probe surfaces. Static pressure sensing ports are positioned on the surfaces of the probe relative to the ridges in regions of pressure disturbances caused by the ridges. The probes can be mounted on opposite sides of the aircraft and pneumatically or electrically connected to average the pressures from selected sets of ports.

REFERENCES:
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patent: 4730487 (1988-03-01), Hagen et al.
patent: 5025661 (1991-06-01), McCormack
patent: 5099686 (1992-03-01), Kohler
patent: 5233865 (1993-08-01), Rossow
patent: 5616861 (1997-04-01), Hagen
patent: 5731507 (1998-03-01), Hagen et al.
patent: 6490510 (2002-12-01), Choisnet
patent: 6609421 (2003-08-01), Cronin et al.
patent: 1 255 118 (2002-11-01), None
patent: WO 99/61923 (1999-12-01), None

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