NACA0012 wind-tunnel characterization

Paper · Project 63

This paper reports 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

Before any measurement was trusted, tracer dynamics and flow fluctuation frequencies were analysed to confirm tracer suitability — a cutoff frequency of 57 kHz against a flow frequency of 83 Hz — and buoyancy effects on visualization accuracy were evaluated.

Surface pressure data were acquired and processed to compute pressure coefficients and lift coefficient distributions, with a full statistical uncertainty analysis applied to the results.

Step response of the measurement system/assets/img/papers/naca0012-step-response.png

Fig. 1 — Step response, v̂(t̂) = 1 − e^(−Kt̂) for K = 4285.

Results

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

Lift coefficient polar with interpolation and data points/assets/img/papers/naca0012-lift-polar.png

Fig. 2 — Lift coefficient polar.

Lift and drag forces per unit span were calculated at L′ = 5.35–7.61 N/m and D′ = 0.32–0.42 N/m, and flow separation effects were analysed through both pressure data and visualization.

Uncertainty

Uncertainty quantification using statistical methods achieved relative uncertainties below 1% across most operating conditions, which is what makes the polar usable as a validation reference rather than a qualitative result.

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