NACA0012 wind-tunnel characterization

Project · Project 63

Experimental aerodynamic testing of a NACA 0012 airfoil in a wind tunnel, combining flow visualization and pressure measurements to characterize aerodynamic performance across a range of angles of attack.

Method

Tracer dynamics and flow fluctuation frequencies were analysed first, confirming tracer suitability with a cutoff frequency of 57 kHz against a flow frequency of 83 Hz, and evaluating buoyancy effects on visualization accuracy. Getting this right is what licenses the visualization to be read as flow rather than as tracer behaviour.

Surface pressure data were then processed to compute pressure coefficients and lift coefficient distributions.

Results

The resulting lift curve exhibits linear behaviour up to 8–10 degrees followed by stall onset, consistent with aerodynamic theory.

Lift and drag forces per unit span were calculated (L′ = 5.35–7.61 N/m, D′ = 0.32–0.42 N/m) and flow separation effects analysed through both pressure data and visualization. Uncertainty quantification using statistical methods achieved relative uncertainties below 1% across most operating conditions.

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