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

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Chapter 3.0 Vehicle Design<br />

3.3 Wing Aerodynamics<br />

The lift and drag coefficients obtained <strong>for</strong> the thick and thin airfoils were compared. Figure 3-61<br />

shows a comparison of the C L values and Figure 3-62 shows a comparison of the c d values.<br />

Figure 3-61: C L Values <strong>for</strong> the Thick and Thin Airfoils<br />

Figure 3-62: C d Values of the Thick and Thin Airfoils<br />

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