Hydrofoil static pressure acquisition at high Reynolds number
Hamel, Joshua M.
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From 1999 through 2001 the University of Michigan carried out an experimental study of the high Reynolds number turbulent flow over a hydrofoil. The high Reynolds number foil, or Hifoil project was carried out in three phases at the U.S. Navy's William B. Morgan Large Cavitation Channel (LCC), the world's largest variable pressure recirculating water tunnel. Several standard flow measurements were made over the course of this project, including surface static pressure field measurements. Static pressure was measured through the use of surface static pressure taps drilled into the foil model at various chordwise and spanwise locations. Pressure data was collected by a custom designed and built static pressure acquisition system, which could automate the process if so desired. The foil model was a modified NACA 16 shape with a chord of 7 feet and a span of 10 ft. The baseline foil was tested at 0, - 1 and + 1 degrees angle of attack measure relative to the foil's flat pressure side. Additional data was collected on the foil with a modified trailing edge shape again at 0 degrees angle of attack. Data was collected at flow speeds ranging from 1.5 to 18.3 m/s and at temperatures ranging from 22 to 40 deg C (70 to 104 deg F), resulting in a chord based Reynolds number range of 3 to 60 million. The Reynolds number range extends from the existing model scale up to full scale for some naval applications. Data is presented here in the form of normalized nondimensional pressure as a function of chordwise location represented in percentage of chord at all the various geometric and flow speed test conditions. In addition a numeric integration of the pressure curves was performed to calculate the pressure lift generated by the foil at the various test conditions. This data is also presented in the form of lift coefficient as a function of foil configuration and Reynolds number.
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