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

Chapter 3.0 Vehicle Design
3.3 Wing Aerodynamics
Figure 3-87: Mesh View 5
Figure 3-88: Mesh View 6
Figure 3-89 shows the residual convergence plot for the steady state wing in unflapping flight.
3.3.1.5.2 Unblown Steady State Case
This section presents results obtained for the case without blowing. Mars atmospheric conditions
were used along with 14 m/s free stream velocity. The wing was assumed to be at “neutral” position.
Figure 3-89 shows the residual convergence plot.
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