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Wind tunnel test of the NACA63-018 airfoil is performed investigating high Reynolds number dynamic stall behaviour at PLCT 1. The foil is tested within the reduced frequency range of k ≃0.03 and Reynolds number range Re=1.5-6M in the linear attached flow range and at stalled mean AoA at moderate harmonic pitch amplitudes. The foil is fitted with one centred high resolution pressure tab distribution and six spanwise distributed low resolution pressure tab sections for evaluation of spanwise correlations. With the additional tunnel instrumentation, cross comparison between different lift-drag estimates will be shown covering gage, airfoil pressure, wall pressure and wakerake, and evaluation of steady vs harmonic spanwise variations.
Mikkelsen et al. (2024) studied this question.