Two-Dimensional Subsonic Experiments with an NACA 0012 Airfoil.
CALSPAN CORP BUFFALO N Y
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Two-dimensional tests were made with a 6-inch chord NACA 0012 section in the Calspan 8-foot Transonic Wind Tunnel to obtain section data with minimum wall interference effects. The measurements included three - component force data, surface pressure distributions and oil flow observations, and were made at Mach numbers ranging from 0.4 to 0.95 and at a chord Reynolds number of 1,000,000. Comparisons of the lift curve data with available theory indicate that the results are within about 1 of being two-dimensional. Modified author abstract
- Test Facilities, Equipment and Methods
- Fluid Mechanics