XFOIL Version 6.96 Calculated polar for: NASA NLF1015 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.1834 0.10145 0.09623 -0.1053 0.9376 0.0312 -10.250 -0.1994 0.09210 0.08691 -0.1110 0.9308 0.0286 -10.000 -0.1967 0.08710 0.08192 -0.1143 0.9266 0.0284 -9.750 -0.1924 0.08147 0.07628 -0.1189 0.9238 0.0281 -9.500 -0.1979 0.07620 0.07102 -0.1217 0.9172 0.0277 -9.250 -0.2110 0.06778 0.06254 -0.1291 0.9113 0.0275 -9.000 -0.2280 0.06254 0.05721 -0.1326 0.9035 0.0270 -8.750 -0.2473 0.05809 0.05260 -0.1349 0.8958 0.0267 -8.500 -0.2700 0.05531 0.04969 -0.1334 0.8856 0.0266 -8.250 -0.2750 0.05111 0.04516 -0.1351 0.8806 0.0266 -8.000 -0.2888 0.04899 0.04281 -0.1320 0.8719 0.0267 -7.750 -0.2841 0.04545 0.03885 -0.1325 0.8674 0.0272 -7.250 -0.2746 0.04051 0.03307 -0.1299 0.8565 0.0281 -7.000 -0.2557 0.03795 0.03008 -0.1303 0.8536 0.0282 -6.750 -0.2307 0.03555 0.02726 -0.1313 0.8518 0.0283 -6.500 -0.2017 0.03344 0.02473 -0.1325 0.8505 0.0286 -6.250 -0.2007 0.03290 0.02401 -0.1284 0.8430 0.0288 -6.000 -0.1771 0.03135 0.02231 -0.1284 0.8402 0.0293 -5.750 -0.1500 0.03003 0.02086 -0.1289 0.8384 0.0300 -5.500 -0.1211 0.02890 0.01964 -0.1297 0.8370 0.0310 -5.250 -0.0906 0.02791 0.01854 -0.1306 0.8358 0.0323 -5.000 -0.0897 0.02807 0.01864 -0.1265 0.8287 0.0337 -4.750 -0.0653 0.02755 0.01797 -0.1264 0.8258 0.0365 -4.500 -0.0366 0.02667 0.01708 -0.1272 0.8239 0.0391 -4.250 -0.0054 0.02596 0.01627 -0.1284 0.8225 0.0425 -4.000 0.0274 0.02528 0.01548 -0.1299 0.8213 0.0482 -3.750 0.0348 0.02551 0.01571 -0.1271 0.8154 0.0559 -3.500 0.0597 0.02498 0.01542 -0.1275 0.8122 0.0965 -3.250 0.0920 0.02402 0.01508 -0.1299 0.8103 0.2272 -3.000 0.1241 0.02289 0.01526 -0.1320 0.8091 0.4876 -2.750 0.1494 0.02320 0.01578 -0.1308 0.8075 0.6062 -2.500 0.1784 0.02345 0.01590 -0.1305 0.8062 0.6433 -2.250 0.1778 0.02461 0.01703 -0.1261 0.7983 0.6604 -2.000 0.2020 0.02497 0.01725 -0.1254 0.7957 0.6821 -1.750 0.2265 0.02524 0.01742 -0.1245 0.7937 0.6991 -1.500 0.2539 0.02537 0.01745 -0.1241 0.7922 0.7144 -1.250 0.2582 0.02635 0.01841 -0.1204 0.7858 0.7254 -1.000 0.2744 0.02685 0.01885 -0.1184 0.7819 0.7368 -0.750 0.2992 0.02702 0.01894 -0.1177 0.7797 0.7489 -0.500 0.3282 0.02709 0.01891 -0.1179 0.7780 0.7604 -0.250 0.3557 0.02708 0.01882 -0.1176 0.7766 0.7686 0.000 0.3549 0.02836 0.02010 -0.1140 0.7680 0.7765 0.250 0.3794 0.02850 0.02020 -0.1135 0.7654 0.7830 0.500 0.4123 0.02853 0.02012 -0.1148 0.7637 0.7900 0.750 0.4418 0.02844 0.01999 -0.1151 0.7622 0.7946 1.250 0.4726 0.02981 0.02133 -0.1126 0.7508 0.8058 1.500 0.5023 0.02978 0.02126 -0.1131 0.7489 0.8099 1.750 0.5355 0.02966 0.02112 -0.1142 0.7474 0.8145 2.250 0.5671 0.03098 0.02246 -0.1118 0.7355 0.8244 2.500 0.5998 0.03087 0.02234 -0.1128 0.7336 0.8291 2.750 0.6358 0.03069 0.02215 -0.1143 0.7322 0.8342 3.250 0.6671 0.03188 0.02343 -0.1116 0.7194 0.8444 3.500 0.7030 0.03163 0.02319 -0.1131 0.7178 0.8500 4.000 0.7363 0.03264 0.02433 -0.1106 0.7048 0.8622 4.250 0.7708 0.03224 0.02398 -0.1115 0.7030 0.8677 4.750 0.8059 0.03301 0.02491 -0.1090 0.6895 0.8830 5.000 0.8411 0.03239 0.02437 -0.1098 0.6878 0.8909 5.250 0.8421 0.03354 0.02562 -0.1065 0.6760 0.9018 5.500 0.8761 0.03283 0.02501 -0.1070 0.6738 0.9121 6.000 0.9137 0.03293 0.02536 -0.1046 0.6594 0.9590 6.500 0.9667 0.03299 0.02561 -0.1052 0.6448 1.0000 6.750 0.9813 0.03388 0.02662 -0.1043 0.6328 1.0000 7.000 1.0216 0.03286 0.02570 -0.1057 0.6295 1.0000 7.500 1.0525 0.03422 0.02727 -0.1037 0.6041 1.0000 7.750 1.0722 0.03455 0.02774 -0.1030 0.5919 1.0000 8.000 1.0951 0.03462 0.02792 -0.1025 0.5798 1.0000 8.250 1.1188 0.03459 0.02801 -0.1020 0.5663 1.0000 8.500 1.1429 0.03453 0.02805 -0.1015 0.5507 1.0000 8.750 1.1701 0.03417 0.02781 -0.1011 0.5331 1.0000 9.000 1.2052 0.03314 0.02680 -0.1012 0.5123 1.0000 9.250 1.2337 0.03271 0.02635 -0.1008 0.4840 1.0000 9.500 1.2590 0.03258 0.02612 -0.1001 0.4495 1.0000 9.750 1.2760 0.03312 0.02653 -0.0986 0.4107 1.0000 10.000 1.2838 0.03439 0.02756 -0.0965 0.3681 1.0000 10.250 1.2848 0.03622 0.02912 -0.0939 0.3234 1.0000 10.500 1.2836 0.03836 0.03100 -0.0914 0.2806 1.0000 10.750 1.2822 0.04065 0.03304 -0.0891 0.2412 1.0000 11.000 1.2808 0.04307 0.03523 -0.0871 0.2026 1.0000 11.250 1.2812 0.04547 0.03742 -0.0853 0.1678 1.0000 11.500 1.2815 0.04798 0.03971 -0.0838 0.1337 1.0000 11.750 1.2833 0.05044 0.04203 -0.0824 0.1054 1.0000 12.000 1.2857 0.05292 0.04439 -0.0812 0.0805 1.0000 12.250 1.2863 0.05566 0.04699 -0.0799 0.0571 1.0000 12.500 1.2870 0.05849 0.04975 -0.0788 0.0419 1.0000 12.750 1.2876 0.06141 0.05267 -0.0777 0.0336 1.0000 13.000 1.2887 0.06435 0.05569 -0.0768 0.0291 1.0000 13.250 1.2887 0.06750 0.05892 -0.0760 0.0265 1.0000 13.500 1.2901 0.07052 0.06213 -0.0753 0.0246 1.0000 13.750 1.2907 0.07370 0.06546 -0.0749 0.0232 1.0000 14.000 1.2905 0.07705 0.06895 -0.0745 0.0221 1.0000 14.250 1.2883 0.08071 0.07275 -0.0743 0.0213 1.0000 14.500 1.2886 0.08412 0.07631 -0.0742 0.0205 1.0000 14.750 1.2901 0.08743 0.07981 -0.0742 0.0196 1.0000 15.000 1.2914 0.09079 0.08333 -0.0744 0.0187 1.0000 15.250 1.2924 0.09424 0.08692 -0.0747 0.0179 1.0000 15.500 1.2931 0.09777 0.09058 -0.0752 0.0173 1.0000 15.750 1.2934 0.10135 0.09427 -0.0758 0.0168 1.0000