초록 ▼

The present invention is a force-based instrument that measures local flow angle. The preferred embodiment of the invention has a low aspect ratio airfoil member connected to a mounting base. Using a series of strain gauges located at the connecting portion of the probe, aerodynamic forces on the ai

The present invention is a force-based instrument that measures local flow angle. The preferred embodiment of the invention has a low aspect ratio airfoil member connected to a mounting base. Using a series of strain gauges located at the connecting portion of the probe, aerodynamic forces on the airfoil member can be converted to strain, which in turn can be converted to local air flow measurements. The present invention has no moving parts and is well suited for measuring flow in a transonic and supersonic regime.

대표청구항 ▼

1. A probe for determining airflow direction comprising: a base adapted to be fixed to a moving body; a symmetric airfoil member having a low aspect ratio fin and a neck portion connecting the fin to the base, and a plurality of strain gauges located on the symmetric airfoil member at upper and

1. A probe for determining airflow direction comprising: a base adapted to be fixed to a moving body; a symmetric airfoil member having a low aspect ratio fin and a neck portion connecting the fin to the base, and a plurality of strain gauges located on the symmetric airfoil member at upper and lower surfaces for the neck portion, the plurality of strain gauges adapted to measure a movement induced force on the fin. 2. The probe of claim 1, wherein the probe comprises no moving parts. 3. The probe of claim 2, wherein the ratio of a chord length of the airfoil member to a thickness of the airfoil member is not greater than eight to one. 4. The probe of claim 2, wherein the strain gauges are comprised of fiber optic wires. 5. The probe of claim 2 wherein the symmetric airfoil member includes a flat upper surface parallel to a flat lower surface. 6. The probe of claim 1 wherein the strain gauges are connected to form a Wheatstone bridge circuit. 7. The probe of claim 1 where the low aspect ratio fin further comprises a leading edge and a trailing edge; where the leading edge and trailing edge have equal apex angles. 8. The probe of claim 1 wherein said base is adapted to be mounted to an aircraft. 9. The probe of claim 8 wherein the movement induced force comprises aerodynamic forces. 10. The probe of claim 1 wherein said base is adapted to be mounted to a ship. 11. The probe of claim 10 wherein the movement induced force comprises hydrodynamic forces. 12. An aerodynamic flow angle probe comprising: a low aspect ratio fin having flat upper and lower surfaces, a first inclined upper face and a first inclined lower face converging at a leading edge, and a second inclined upper face and a second inclined lower face converging at a trailing edge, and a neck portion extending from the flat upper and lower surfaces; a base for mounting the low aspect ratio fin perpendicular to a mounting surface; and a plurality of strain detecting fiber optic wires mounted on the low aspect ratio fin along the flat upper and lower surfaces. 13. The aerodynamic flow angle probe of claim 12 where the distance between the flat upper surface and the flat lower surface of the low aspect ratio fin is less than one eighth of one inch. 14. The aerodynamic flow angle probe of claim 12 wherein a voltage signal is produced by the fiber optic wires indicative of a force applied to the low aspect ratio fin. 15. A fluid flow probe comprising: a base adapted to be fixed to a moving body; an airfoil member having a fin, with an upper and lower surface, and a neck connecting the fin to the base; and, a plurality of strain-detecting fiber optic wires mounted to the upper and lower surfaces of the fin. 16. The fluid flow probe of claim 15 where the upper and lower surfaces of the fin are flat and separated by a distance of less than one eighth of one inch.