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

Chapter 3.0 Vehicle Design
3.3 Wing Aerodynamics
Table 3-9: Design of Experiment Array (Continued)
Run No. Span Velocity Frequency
Plunge
Amplitude
Pitch
Amplitude
22 3.3 26 11 60 10
23 3.3 20 6 60 10
24 3.3 20 16 60 10
25 3.3 20 11 45 10
26 3.3 20 11 75 10
27 3.3 20 11 60 8
28 3.3 20 11 60 12
The code written for analysis was executed for all 28 combinations to evaluate the response variables.
The results for lift, moment and power are given in Figures 3-125, 3-126, and 3-127,
respectively. These results can be used in many a ways. For example, keeping all the variables at
fixed level for each dimension and just varying one variable can help determine the relation of a
specific variable with the response variable. Also these results can be used to assess the optimum
configuration in the design space. Also, a Multiple Analysis of Variance (MANOVA) can
be performed to evaluate the response variables as response surface equations (RSE) in terms of
the control variables. Because a quadratic relation was assumed in each dimension, and a fractional
factorial array was used, only first and second order main effects and first order interactions
can be included in the RSEs. These RSEs, in addition to having these five variables, would
still be time-dependant within each time period.
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