XFOIL Version 6.94 Calculated polar for: SD2030-086-88 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2883 0.00631 0.00260 -0.0644 0.8788 0.9626 0.500 0.3712 0.00626 0.00246 -0.0695 0.8635 0.9800 1.000 0.4604 0.00618 0.00230 -0.0764 0.8437 0.9901 1.500 0.5405 0.00613 0.00215 -0.0816 0.8184 0.9997 2.000 0.5839 0.00613 0.00208 -0.0790 0.7861 1.0000 2.500 0.6241 0.00623 0.00206 -0.0756 0.7430 1.0000 3.000 0.6616 0.00650 0.00212 -0.0716 0.6777 1.0000 3.500 0.6951 0.00710 0.00230 -0.0669 0.5791 1.0000 4.000 0.7285 0.00801 0.00268 -0.0625 0.4601 1.0000 4.500 0.7668 0.00901 0.00321 -0.0593 0.3515 1.0000 5.000 0.8087 0.00999 0.00378 -0.0570 0.2600 1.0000 5.500 0.8524 0.01093 0.00441 -0.0551 0.1898 1.0000 6.000 0.8968 0.01186 0.00514 -0.0533 0.1347 1.0000 6.500 0.9407 0.01288 0.00597 -0.0514 0.0918 1.0000 7.000 0.9844 0.01391 0.00692 -0.0495 0.0661 1.0000 7.500 1.0282 0.01491 0.00797 -0.0476 0.0516 1.0000 8.000 1.0716 0.01589 0.00898 -0.0457 0.0402 1.0000 8.500 1.1152 0.01682 0.00995 -0.0439 0.0276 1.0000 9.000 1.1471 0.01894 0.01208 -0.0401 0.0138 1.0000 9.500 1.1807 0.02066 0.01404 -0.0366 0.0114 1.0000 10.000 1.2044 0.02284 0.01642 -0.0317 0.0101 1.0000 10.500 1.2117 0.02655 0.02048 -0.0249 0.0091 1.0000 11.000 1.2317 0.02900 0.02323 -0.0204 0.0087 1.0000 11.500 1.2419 0.03245 0.02706 -0.0153 0.0083 1.0000 12.000 1.2431 0.03676 0.03179 -0.0103 0.0081 1.0000 12.500 1.2335 0.04224 0.03775 -0.0060 0.0079 1.0000 13.000 1.2155 0.04896 0.04490 -0.0035 0.0078 1.0000 13.500 1.1884 0.05772 0.05409 -0.0038 0.0076 1.0000 14.000 1.1537 0.06947 0.06625 -0.0084 0.0077 1.0000 14.500 1.1134 0.08527 0.08242 -0.0178 0.0077 1.0000 15.000 1.0651 0.10625 0.10371 -0.0314 0.0081 1.0000 15.500 1.0053 0.13290 0.13061 -0.0473 0.0085 1.0000 17.000 0.8991 0.21130 0.20892 -0.0835 0.0171 1.0000 17.500 0.9116 0.21943 0.21706 -0.0879 0.0160 1.0000 18.000 0.9260 0.22654 0.22417 -0.0918 0.0151 1.0000 18.500 0.9425 0.23281 0.23048 -0.0948 0.0145 1.0000 19.000 0.9522 0.24317 0.24081 -0.0993 0.0139 1.0000 19.500 0.9657 0.25138 0.24901 -0.1041 0.0138 1.0000 20.000 0.9790 0.25904 0.25667 -0.1092 0.0136 1.0000 20.500 0.9922 0.26728 0.26489 -0.1152 0.0123 1.0000 21.000 1.0070 0.27452 0.27214 -0.1197 0.0113 1.0000 21.500 1.0219 0.28134 0.27897 -0.1240 0.0106 1.0000 22.000 1.0368 0.28765 0.28528 -0.1282 0.0100 1.0000 22.500 1.0522 0.29328 0.29094 -0.1317 0.0095 1.0000 23.000 1.0665 0.30181 0.29949 -0.1354 0.0091 1.0000 23.500 1.0802 0.30856 0.30623 -0.1403 0.0090 1.0000 24.000 1.0934 0.31527 0.31293 -0.1459 0.0088 1.0000 24.500 1.1087 0.32245 0.32012 -0.1510 0.0076 1.0000 25.000 1.1228 0.32879 0.32646 -0.1555 0.0070 1.0000 25.500 1.1365 0.33480 0.33248 -0.1599 0.0065 1.0000 26.000 1.1499 0.34045 0.33815 -0.1644 0.0061 1.0000 26.500 1.1629 0.34588 0.34360 -0.1687 0.0058 1.0000 27.000 1.1758 0.35156 0.34932 -0.1726 0.0056 1.0000