XFOIL Version 6.96 Calculated polar for: FX 76-MP-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 0.1597 0.08841 0.08464 -0.1525 0.7948 0.0106 -10.000 0.1672 0.08554 0.08177 -0.1539 0.7927 0.0106 -9.750 0.1737 0.08247 0.07871 -0.1554 0.7906 0.0108 -9.500 0.1808 0.07958 0.07580 -0.1568 0.7885 0.0106 -8.500 0.0051 0.02259 0.01819 -0.2004 0.7728 0.0125 -8.250 0.0288 0.02067 0.01601 -0.2022 0.7709 0.0128 -8.000 0.0533 0.01919 0.01431 -0.2033 0.7690 0.0132 -7.750 0.0785 0.01792 0.01282 -0.2042 0.7670 0.0137 -7.500 0.1045 0.01679 0.01147 -0.2049 0.7651 0.0142 -7.250 0.1311 0.01587 0.01034 -0.2055 0.7630 0.0147 -7.000 0.1581 0.01506 0.00934 -0.2060 0.7610 0.0153 -6.750 0.1855 0.01453 0.00872 -0.2064 0.7591 0.0160 -6.500 0.2134 0.01416 0.00826 -0.2068 0.7574 0.0169 -6.250 0.2416 0.01371 0.00767 -0.2072 0.7558 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0.00392 -0.2028 0.6175 1.0000 3.750 1.3042 0.00922 0.00404 -0.2018 0.6090 1.0000 4.000 1.3268 0.00938 0.00417 -0.2010 0.5997 1.0000 4.250 1.3482 0.00958 0.00433 -0.1998 0.5906 1.0000 4.500 1.3687 0.00979 0.00451 -0.1985 0.5802 1.0000 4.750 1.3886 0.01001 0.00469 -0.1971 0.5696 1.0000 5.000 1.4053 0.01026 0.00491 -0.1950 0.5585 1.0000 5.250 1.4201 0.01057 0.00516 -0.1926 0.5460 1.0000 5.500 1.4350 0.01090 0.00544 -0.1902 0.5337 1.0000 5.750 1.4493 0.01126 0.00576 -0.1878 0.5204 1.0000 6.000 1.4635 0.01164 0.00610 -0.1854 0.5079 1.0000 6.250 1.4774 0.01205 0.00649 -0.1830 0.4964 1.0000 6.500 1.4900 0.01253 0.00694 -0.1805 0.4845 1.0000 6.750 1.5010 0.01309 0.00745 -0.1777 0.4715 1.0000 7.000 1.5128 0.01367 0.00800 -0.1753 0.4588 1.0000 7.250 1.5235 0.01434 0.00863 -0.1727 0.4451 1.0000 7.500 1.5348 0.01503 0.00931 -0.1703 0.4324 1.0000 7.750 1.5463 0.01576 0.01002 -0.1681 0.4209 1.0000 8.000 1.5572 0.01657 0.01081 -0.1658 0.4095 1.0000 8.250 1.5673 0.01747 0.01168 -0.1636 0.3969 1.0000 8.500 1.5787 0.01834 0.01255 -0.1616 0.3847 1.0000 8.750 1.5902 0.01925 0.01345 -0.1597 0.3736 1.0000 9.000 1.5996 0.02031 0.01448 -0.1576 0.3607 1.0000 9.250 1.6088 0.02141 0.01556 -0.1555 0.3481 1.0000 9.500 1.6184 0.02251 0.01665 -0.1536 0.3366 1.0000 9.750 1.6279 0.02364 0.01777 -0.1517 0.3238 1.0000 10.000 1.6371 0.02481 0.01894 -0.1497 0.3117 1.0000 10.250 1.6439 0.02617 0.02026 -0.1476 0.2972 1.0000 10.500 1.6476 0.02777 0.02179 -0.1452 0.2793 1.0000 10.750 1.6494 0.02954 0.02348 -0.1427 0.2604 1.0000 11.000 1.6518 0.03133 0.02519 -0.1404 0.2401 1.0000 11.250 1.6513 0.03338 0.02712 -0.1379 0.2182 1.0000 11.500 1.6522 0.03538 0.02903 -0.1356 0.1973 1.0000 11.750 1.6528 0.03748 0.03104 -0.1334 0.1777 1.0000 12.000 1.6538 0.03959 0.03306 -0.1313 0.1599 1.0000 12.250 1.6543 0.04180 0.03519 -0.1293 0.1410 1.0000 12.500 1.6555 0.04401 0.03733 -0.1275 0.1249 1.0000 12.750 1.6554 0.04638 0.03963 -0.1256 0.1086 1.0000 13.000 1.6562 0.04875 0.04196 -0.1239 0.0948 1.0000 13.250 1.6554 0.05131 0.04446 -0.1222 0.0795 1.0000 13.500 1.6538 0.05403 0.04713 -0.1206 0.0654 1.0000 13.750 1.6528 0.05676 0.04984 -0.1192 0.0540 1.0000 14.000 1.6515 0.05959 0.05265 -0.1178 0.0438 1.0000 14.250 1.6491 0.06260 0.05564 -0.1166 0.0345 1.0000 14.500 1.6482 0.06553 0.05858 -0.1155 0.0278 1.0000 14.750 1.6477 0.06849 0.06157 -0.1146 0.0224 1.0000 15.000 1.6473 0.07149 0.06460 -0.1138 0.0184 1.0000 15.250 1.6463 0.07464 0.06781 -0.1131 0.0153 1.0000 15.500 1.6464 0.07769 0.07092 -0.1125 0.0129 1.0000 15.750 1.6468 0.08076 0.07407 -0.1120 0.0114 1.0000 16.000 1.6467 0.08398 0.07736 -0.1117 0.0101 1.0000 16.500 1.6459 0.09061 0.08416 -0.1114 0.0083 1.0000 16.750 1.6448 0.09410 0.08774 -0.1114 0.0076 1.0000 17.000 1.6429 0.09775 0.09148 -0.1115 0.0071 1.0000 17.250 1.6403 0.10156 0.09539 -0.1118 0.0067 1.0000 17.500 1.6393 0.10517 0.09912 -0.1122 0.0064 1.0000 17.750 1.6373 0.10898 0.10304 -0.1127 0.0060 1.0000 18.000 1.6347 0.11291 0.10708 -0.1134 0.0057 1.0000 18.250 1.6319 0.11692 0.11119 -0.1142 0.0055 1.0000 18.500 1.6282 0.12107 0.11544 -0.1151 0.0052 1.0000 18.750 1.6237 0.12541 0.11988 -0.1163 0.0050 1.0000 19.000 1.6186 0.12990 0.12448 -0.1176 0.0049 1.0000