Abstract
A family of single-element, NACA 0012 wings was computationally studied to find a correlation between mean flow parameters and the noise produced by the wingtip. An incompressible NavierStokes flow solver was used to compute the flowfleld. Dimensional analysis suggested combinations of mean flow parameters that could consistently scale with the wingtip noise. Correlations were formed between the computed flow variables and experimentally measured sound pressure levels. The results suggest that wingtip noise scales with an appropriate integral of the eighth power of the velocity multiplied by the thickness of the wing. Combinations of two freestream flow velocities (39.6 and 78.1 m/s), three angles of attack (5.4, 10.8, and 14.4 deg.), and five aspect ratios (2, 2.67, 4, 6, 12) defined the regime investigated. To further validate the correlations, an additional wing was experimentally and computationally investigated at four angles of attack (0, 4, 8, and 12 deg.) and three freestream velocities (30, 40, and 50 m/s). The eighth power of velocity correlation held for the second configuration as well.
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