Lift and Drag Coefficient Analysis
The lift and drag coefficients are important parameters in evaluating the flying performances. The average values are taken down and plotted in Figure 1 and Figure 2. The difference between the largest value and smallest value are treated as the error off the averaged value.
In Figure 1, all lift coefficients show the ascending trends. For the entire range, the curved plate generally has the largest lift coefficient and NACA 0012 has the lowest. It can be noticed that lift coefficient does not get enhanced due to the leading edge vortex for curved plate at angle of attack 2, 3 and 4 degrees. Instead, it is lower than that was expected (see the blue line in Figure 1)
In Figure 1, all lift coefficients show the ascending trends. For the entire range, the curved plate generally has the largest lift coefficient and NACA 0012 has the lowest. It can be noticed that lift coefficient does not get enhanced due to the leading edge vortex for curved plate at angle of attack 2, 3 and 4 degrees. Instead, it is lower than that was expected (see the blue line in Figure 1)
For the drag coefficients, the flat plate has generally the highest values and the NACA0012 has the lowest. For the cases where leading edge vortex exists, the drag coefficient seems to be higher than the trend (indicated as the blue line in Figure 2).
The error bars for both lift and drag coefficients are low for the curved plate at the angle of attack 2, 3 and 4 degrees. This can be considered as the evidence that the leading edge vortex is a steady feature.
The error bars for both lift and drag coefficients are low for the curved plate at the angle of attack 2, 3 and 4 degrees. This can be considered as the evidence that the leading edge vortex is a steady feature.