Aerodynamics and Design for Ultra-Low Reynolds Number Flight

Thrust (g)
4.5
4.0
3.5
3.0
2.5
2.0
1.5
1.0
0.5
0.0
Reduced-order Method
Experiment
Reduced-order Method, Original +3 deg.
Experiment, Original +3 deg.
Modeled w/ Torsional Defl.
Modeled w/ Torsional Defl., +3 deg.
10000 20000 30000
RPM
40000 50000
Chapter 6
FIGURE 6.31 Comparison of experimental and predicted thrust with torsional deflections for two
versions of the five-blade 2.2cm rotor.
The rapid analysis method thrust predictions for the deflected forms are presented with
the experimental results and the undeflected predicted performance in Figure 6.31. Here
the agreement is not as good as in the four-blade case, but the overall trend is well
captured considering that only two iterations on the aerodynamic forces were performed.
Performance analysis of these deflected forms reinforces the importance of torsional
effects and the ability of the current tools to capture them. It also provides closure on the
most anomalous experimental behavior observed over the course of this research.
6.6 Spanwise Thrust and Torque Distributions
The experimental results have so far limited the discussion of performance to the gross
performance parameters of total thrust and total power required. Three-dimensional
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