Phase II Final Report - NASA's Institute for Advanced Concepts

Chapter 3.0 Vehicle Design
3.3 Wing Aerodynamics
3
2
Coefficient of Lift (CL)
1
0
0.000 0.020 0.040 0.060 0.080 0.100 0.120 0.140 0.160 0.180
-1
Case26
Case25
-2
-3
Time (t) in secs
Figure 3-131: Variation of Lift Coefficient with Flapping Amplitude
It can be seen that by increasing the flapping amplitude, the results improve for the upbeat,
but this has a negative influence for the down beat. The effect on thrust is just the opposite,
with increased thrust being realized on the down beat.
e. Changing Pitching amplitude alone while keeping the rest of the variables fixed results
in that which is depicted in Case 27 and Case 28 of design-of-experiments array. The
results are shown in Figure 3-132.
149