XFOIL Version 6.94 Calculated polar for: Eiffel 371 (Monge) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2871 0.01119 0.00488 -0.0351 0.6068 0.7976 0.500 0.3383 0.01140 0.00494 -0.0341 0.5911 0.8041 1.000 0.3897 0.01153 0.00499 -0.0331 0.5751 0.8098 1.500 0.4401 0.01172 0.00505 -0.0321 0.5581 0.8144 2.000 0.4905 0.01186 0.00507 -0.0311 0.5406 0.8190 2.500 0.5388 0.01202 0.00518 -0.0297 0.5219 0.8240 3.000 0.5869 0.01211 0.00522 -0.0284 0.5025 0.8283 3.500 0.6336 0.01225 0.00534 -0.0268 0.4811 0.8326 4.000 0.6783 0.01240 0.00543 -0.0250 0.4557 0.8361 4.500 0.7225 0.01260 0.00557 -0.0231 0.4289 0.8384 5.000 0.7647 0.01291 0.00579 -0.0211 0.3999 0.8400 5.500 0.8066 0.01334 0.00612 -0.0191 0.3747 0.8410 6.000 0.8480 0.01383 0.00654 -0.0171 0.3534 0.8420 6.500 0.8879 0.01437 0.00702 -0.0150 0.3351 0.8431 7.000 0.9256 0.01491 0.00754 -0.0125 0.3184 0.8443 7.500 0.9631 0.01547 0.00812 -0.0100 0.3027 0.8450 8.000 0.9986 0.01608 0.00877 -0.0073 0.2861 0.8458 8.500 1.0313 0.01680 0.00951 -0.0044 0.2691 0.8465 9.000 1.0627 0.01754 0.01033 -0.0014 0.2490 0.8470 9.500 1.0880 0.01854 0.01133 0.0023 0.2244 0.8475 10.000 1.1098 0.01979 0.01255 0.0061 0.1999 0.8479 10.500 1.1296 0.02129 0.01402 0.0097 0.1818 0.8484 11.000 1.1504 0.02285 0.01562 0.0128 0.1668 0.8493 11.500 1.1699 0.02465 0.01749 0.0155 0.1556 0.8496 12.000 1.1875 0.02673 0.01965 0.0178 0.1443 0.8500 12.500 1.2021 0.02920 0.02221 0.0198 0.1325 0.8504 13.000 1.2139 0.03215 0.02525 0.0213 0.1162 0.8506 13.500 1.2223 0.03572 0.02884 0.0223 0.0967 0.8507 14.500 1.1733 0.05028 0.04307 0.0238 0.0237 0.8501 15.000 1.1559 0.05791 0.05091 0.0229 0.0198 0.8500 15.500 1.1410 0.06584 0.05912 0.0212 0.0187 0.8498 16.000 1.1203 0.07519 0.06877 0.0184 0.0173 0.8497 16.500 1.1016 0.08489 0.07876 0.0150 0.0170 0.8495 17.000 1.0821 0.09521 0.08936 0.0110 0.0169 0.8494 17.500 1.0578 0.10672 0.10113 0.0063 0.0166 0.8492 18.000 1.0312 0.11898 0.11362 0.0011 0.0161 0.8490 18.500 1.0138 0.12985 0.12467 -0.0040 0.0158 0.8490 19.000 1.0035 0.13932 0.13421 -0.0086 0.0151 0.8490 19.500 1.0197 0.14304 0.13784 -0.0110 0.0144 0.8496 20.000 1.0277 0.14940 0.14435 -0.0148 0.0135 0.8502 20.500 1.0469 0.15305 0.14808 -0.0174 0.0130 0.8509 21.000 1.0694 0.15578 0.15086 -0.0195 0.0126 0.8513 21.500 1.0894 0.15894 0.15410 -0.0218 0.0121 0.8517 22.000 1.1160 0.15982 0.15500 -0.0223 0.0113 0.8522 22.500 1.1094 0.16918 0.16467 -0.0284 0.0112 0.8523 23.000 1.1136 0.17577 0.17147 -0.0327 0.0113 0.8527 23.500 1.1102 0.18420 0.18014 -0.0381 0.0113 0.8529 24.000 1.1028 0.19420 0.19039 -0.0451 0.0116 0.8532 25.500 0.7214 0.27502 0.27272 -0.0783 0.0261 0.8554 26.000 0.7216 0.28414 0.28185 -0.0827 0.0224 0.8556 27.000 0.7317 0.29950 0.29727 -0.0897 0.0186 0.8565 27.500 0.7384 0.30655 0.30436 -0.0928 0.0179 0.8571 28.000 0.7399 0.31635 0.31419 -0.0967 0.0159 0.8576 28.500 0.7483 0.32152 0.31942 -0.0997 0.0147 0.8583 29.000 0.7541 0.32914 0.32707 -0.1028 0.0144 0.8591 29.500 0.7546 0.33961 0.33756 -0.1067 0.0126 0.8599 30.000 0.7601 0.34626 0.34427 -0.1099 0.0119 0.8612 30.500 0.7690 0.35155 0.34961 -0.1124 0.0114 0.8631 31.000 0.7679 0.36273 0.36083 -0.1165 0.0110 0.8652 31.500 0.7718 0.37092 0.36908 -0.1197 0.0098 0.8677 32.000 0.7758 0.37786 0.37609 -0.1229 0.0094 0.8715 33.000 0.7702 0.38754 0.38595 -0.1236 0.0084 1.0000 33.500 0.7737 0.39512 0.39356 -0.1270 0.0080 1.0000 34.000 0.7769 0.40239 0.40086 -0.1302 0.0075 1.0000 34.500 0.7801 0.40889 0.40739 -0.1334 0.0072 1.0000 35.000 0.7825 0.41681 0.41533 -0.1366 0.0070 1.0000 35.500 0.7845 0.42582 0.42436 -0.1398 0.0066 1.0000 36.000 0.7865 0.43325 0.43182 -0.1429 0.0061 1.0000 36.500 0.7883 0.44026 0.43886 -0.1461 0.0058 1.0000 37.000 0.7897 0.44670 0.44532 -0.1492 0.0055 1.0000 38.000 0.7917 0.46218 0.46085 -0.1553 0.0053 1.0000 38.500 0.7925 0.46988 0.46858 -0.1583 0.0049 1.0000 39.000 0.7927 0.47663 0.47536 -0.1613 0.0047 1.0000 39.500 0.7927 0.48323 0.48198 -0.1643 0.0044 1.0000 40.000 0.7923 0.48919 0.48797 -0.1673 0.0042 1.0000 41.000 0.7908 0.50298 0.50180 -0.1730 0.0040 1.0000 41.500 0.7901 0.50994 0.50879 -0.1759 0.0039 1.0000 42.000 0.7887 0.51616 0.51504 -0.1787 0.0037 1.0000 42.500 0.7869 0.52207 0.52098 -0.1814 0.0034 1.0000 43.000 0.7849 0.52769 0.52662 -0.1842 0.0033 1.0000 43.500 0.7826 0.53303 0.53198 -0.1870 0.0032 1.0000 45.000 0.7743 0.54958 0.54860 -0.1949 0.0029 1.0000 45.500 0.7713 0.55495 0.55400 -0.1975 0.0028 1.0000 46.000 0.7678 0.55977 0.55884 -0.2000 0.0026 1.0000 46.500 0.7639 0.56416 0.56326 -0.2026 0.0025 1.0000 47.000 0.7599 0.56829 0.56741 -0.2051 0.0024 1.0000 47.500 0.7554 0.57206 0.57120 -0.2076 0.0023 1.0000