Research Article

Influence of Thickness Variation on the Flapping Performance of Symmetric NACA Airfoils in Plunging Motion

Table 1

Values of 𝐴 𝑖 for different 𝑥 0 / 𝑐 .

No.Loc ( 𝑥 0 / 𝑐 ) 𝐴 0 𝐴 1 𝐴 2

130.0%0.172110353782670.138679724427170.15458446304747
235.0%0.172110353782670.117589143392500.24333708636138
340.0%0.172110353782670.104178784553620.28842711913075
445.0%0.172110353782670.093534600353750.31733390835548
550.0%0.172110353782670.082448087444490.34181598126744