Aerodynamics and Design for Ultra-Low Reynolds Number Flight

3.5 Effect of Leading Edge Shape and Constant
Thickness Profiles
Chapter 3
Manufacturing limitations at small scales place minimum gage constraints on the design
of highly detailed cross-sections. For very small chord-lengths, the choice must be made
between a traditional airfoil profile, at the expense of greater maximum thickness, or a
constant thickness distribution at the minimum gage. This trade has been explored by
comparing the performance of the NACA 0002 airfoil with 2% constant thickness plates.
Two leading edge shapes are considered for the plates: a leading edge radius and a nearly
blunt leading edge. The trailing edge begins as a radius at 99% chord, but is brought to a
point to simplify grid generation. The three edge shapes are shown in Figure 3.16.
Blunt Leading Edge
Trailing Edge
Radiused Leading Edge
FIGURE 3.16 Leading and trailing edge shapes used in the generation of constant thickness
airfoils.
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