Obtain the time variation of the lift and propulsive force coefficients and their plots for the airfoil given by Example 8.5. Assume that the profile pitches about quarter chord point.

Example 8.5

Assume an airfoil pitching about its leading edge and plunging with \(k=0.35\) as follows

\[
\begin{aligned}
& h=1.1 \cos (\omega t) \\
& \alpha=10^{\circ}+10^{\circ} \cos (\omega t+\pi / 2)
\end{aligned}
\]

Transcribed Image Text:

2 h* nid n Difference (%) (Ref) (%) 0.45 73 58.5 20 15.4 82.4 0.57 79 63.8 20 21 86.7