Table 11 Comparison of \(D/\rho\) between the impulse equation and OpenFOAM results for a NACA 0012 airfoil at \(\alpha =10^{\circ }\) having BC-3 and \(A=30\). All quantities have units of m³s⁻¹.  \(I_2 = 3.33163\) m³s⁻¹at the inlet and the direct determination of drag gives \(D = 17.14205\) m³s⁻¹

x

\(-\int _{\varvec{x}} \varvec{U}_{\varvec{\infty }} \varvec{u} \textbf{d}\varvec{y}\)

\(-\int _{\varvec{x}} \frac{\varvec{1}}{\varvec{2}}\varvec{u}^{\varvec{2}} \textbf{d}\varvec{y}\)

\(\int _{\varvec{x}} \frac{\varvec{1}}{\varvec{2}} \varvec{v}^{\varvec{2}} \textbf{d}\varvec{y}\)

\(-\int _{\varvec{x}} \varvec{y(U}_{\varvec{\infty }}\varvec{+u)\Omega } \textbf{d}y\)

\(\varvec{D/\rho }\) (Eq. (22))