Table 3 Experimental data for a NACA 0012 airfoil at different values of \(\alpha\), \(Re = 5.95 \times 10^6\), Mach number of 0.15 and grit size 80 [22]
From: Some effects of domain size and boundary conditions on the accuracy of airfoil simulations
\(\varvec{\alpha } \varvec{=} \varvec{4.04}^{\varvec{\circ }}\) | \(\varvec{\alpha } \varvec{=} \varvec{6.09}^{\varvec{\circ }}\) | \(\varvec{\alpha } \varvec{=} \varvec{10.12}^{\varvec{\circ }}\) | \(\varvec{\alpha } \varvec{=} \varvec{14.22}^{\varvec{\circ }}\) | |
|---|---|---|---|---|
\(C_{\textrm{d}}\) | 0.00823 | 0.00885 | 0.01201 | 0.01625 |
\(C_{\textrm{l}}\) | 0.4316 | 0.6546 | 1.0707 | 1.4365 |