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Theoretical analyses of six airfoils--the E 387, FX 63-137, S822, S834, SD2030, and SH3055--have been performed for Reynolds numbers from 0.10 x 106 to 1.00 x 106 using the Eppler Airfoil Design and Analysis Code and the XFOIL code. The results from both codes exhibit the typical Reynolds number and roughness effects. Comparisons of the results from the two codes generally show good agreement, particularly for Reynolds numbers greater than 0.10 x 106. The maximum lift coefficient predicted by the XFOIL code is about 0.2 higher, and the Reynolds number and roughness effects are larger. The magnitudes of the zero-lift angle and pitching-moment coefficients predicted by the Eppler code are greater. This work has been selected by scholars as being culturally important, and is part of the knowledge base of civilization as we know it. This work was reproduced from the original artifact, and remains as true to the original work as possible. Therefore, you will see the original copyright references, library stamps (as most of these works have been housed in our most important libraries around the world), and other notations in the work. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. As a reproduction of a historical artifact, this work may contain missing or blurred pages, poor pictures, errant marks, etc. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.

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