FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il) Reynolds number: 200,000 Max Cl/Cd: 84.23 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601001-il-200000.txt Download as CSV file: xf-fx601001-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 (126) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3815 0.08936 0.08593 -0.0391 1.0000 0.0536
-8.500 -0.3958 0.08529 0.08196 -0.0433 1.0000 0.0550
-8.250 -0.4127 0.08160 0.07837 -0.0451 1.0000 0.0553
-8.000 -0.4316 0.07747 0.07435 -0.0471 1.0000 0.0554
-7.750 -0.4477 0.07282 0.06970 -0.0521 1.0000 0.0555
-7.500 -0.4599 0.06892 0.06571 -0.0552 1.0000 0.0555
-7.000 -0.4702 0.05867 0.05556 -0.0552 1.0000 0.0573
-6.750 -0.4672 0.05576 0.05265 -0.0549 1.0000 0.0581
-6.500 -0.4618 0.05260 0.04943 -0.0556 1.0000 0.0592
-6.250 -0.4161 0.03297 0.02811 -0.0738 0.9966 0.0316
-6.000 -0.3734 0.02969 0.02410 -0.0789 0.9935 0.0329
-5.750 -0.3363 0.02542 0.01934 -0.0824 0.9905 0.0324
-5.500 -0.2973 0.02261 0.01607 -0.0853 0.9873 0.0326
-5.250 -0.2591 0.01959 0.01274 -0.0879 0.9850 0.0340
-5.000 -0.2199 0.01836 0.01146 -0.0905 0.9819 0.0378
-4.750 -0.1837 0.01767 0.01060 -0.0922 0.9765 0.0428
-4.500 -0.1446 0.01610 0.00907 -0.0948 0.9731 0.0516
-4.250 -0.1020 0.01483 0.00783 -0.0983 0.9702 0.0781
-4.000 -0.0653 0.01406 0.00709 -0.1005 0.9644 0.1019
-3.750 -0.0255 0.01340 0.00656 -0.1034 0.9596 0.1399
-3.500 0.0172 0.01197 0.00624 -0.1075 0.9568 0.3807
-3.250 0.0533 0.01225 0.00651 -0.1088 0.9501 0.4566
-3.000 0.0930 0.01248 0.00662 -0.1108 0.9446 0.4874
-2.750 0.1364 0.01255 0.00657 -0.1135 0.9413 0.5085
-2.500 0.1686 0.01258 0.00653 -0.1141 0.9330 0.5245
-2.250 0.2066 0.01252 0.00649 -0.1156 0.9281 0.5431
-2.000 0.2382 0.01248 0.00646 -0.1159 0.9198 0.5592
-1.750 0.2732 0.01237 0.00636 -0.1168 0.9135 0.5751
-1.500 0.3031 0.01227 0.00623 -0.1168 0.9040 0.5866
-1.250 0.3375 0.01207 0.00597 -0.1177 0.8974 0.5950
-1.000 0.3657 0.01192 0.00579 -0.1174 0.8861 0.6008
-0.750 0.3946 0.01178 0.00563 -0.1172 0.8753 0.6068
-0.500 0.4243 0.01165 0.00541 -0.1172 0.8644 0.6127
-0.250 0.4521 0.01148 0.00524 -0.1166 0.8514 0.6182
0.000 0.4799 0.01140 0.00507 -0.1161 0.8368 0.6262
0.250 0.5067 0.01131 0.00498 -0.1154 0.8227 0.6326
0.500 0.5346 0.01129 0.00490 -0.1151 0.8097 0.6390
0.750 0.5623 0.01126 0.00482 -0.1148 0.7968 0.6435
1.000 0.5895 0.01125 0.00481 -0.1144 0.7830 0.6478
1.250 0.6169 0.01125 0.00477 -0.1141 0.7686 0.6522
1.500 0.6442 0.01125 0.00471 -0.1137 0.7531 0.6568
1.750 0.6706 0.01124 0.00471 -0.1131 0.7360 0.6613
2.000 0.6976 0.01126 0.00471 -0.1128 0.7202 0.6662
2.250 0.7250 0.01131 0.00474 -0.1125 0.7062 0.6712
2.500 0.7520 0.01135 0.00481 -0.1122 0.6926 0.6765
2.750 0.7793 0.01143 0.00490 -0.1119 0.6792 0.6829
3.000 0.8061 0.01151 0.00500 -0.1115 0.6654 0.6886
3.250 0.8329 0.01160 0.00512 -0.1112 0.6505 0.6956
3.500 0.8594 0.01169 0.00525 -0.1108 0.6347 0.7034
3.750 0.8859 0.01180 0.00543 -0.1104 0.6186 0.7132
4.000 0.9119 0.01190 0.00560 -0.1098 0.6020 0.7234
4.250 0.9377 0.01202 0.00579 -0.1093 0.5845 0.7363
4.500 0.9630 0.01215 0.00596 -0.1086 0.5656 0.7541
4.750 0.9871 0.01220 0.00616 -0.1077 0.5416 0.7820
5.000 1.0049 0.01193 0.00621 -0.1052 0.5157 1.0000
5.250 1.0307 0.01224 0.00642 -0.1048 0.4817 1.0000
5.500 1.0549 0.01261 0.00667 -0.1042 0.4409 1.0000
5.750 1.0765 0.01319 0.00701 -0.1031 0.3906 1.0000
6.000 1.0967 0.01396 0.00749 -0.1020 0.3406 1.0000
6.250 1.1175 0.01473 0.00803 -0.1010 0.2987 1.0000
6.500 1.1387 0.01546 0.00859 -0.1001 0.2629 1.0000
6.750 1.1605 0.01613 0.00915 -0.0993 0.2292 1.0000
7.000 1.1815 0.01687 0.00979 -0.0984 0.1956 1.0000
7.250 1.1994 0.01799 0.01061 -0.0972 0.1375 1.0000
7.500 1.2045 0.02075 0.01258 -0.0943 0.0453 1.0000
7.750 1.2196 0.02224 0.01409 -0.0923 0.0364 1.0000
8.000 1.2352 0.02352 0.01546 -0.0905 0.0325 1.0000
8.250 1.2443 0.02541 0.01740 -0.0880 0.0299 1.0000
8.500 1.2573 0.02697 0.01906 -0.0858 0.0285 1.0000
8.750 1.2724 0.02827 0.02050 -0.0840 0.0266 1.0000
9.000 1.2863 0.02968 0.02199 -0.0822 0.0248 1.0000
9.250 1.2991 0.03137 0.02374 -0.0803 0.0238 1.0000
9.500 1.3134 0.03336 0.02579 -0.0786 0.0230 1.0000
9.750 1.3331 0.03612 0.02863 -0.0778 0.0222 1.0000
10.000 1.3564 0.03977 0.03247 -0.0775 0.0218 1.0000
10.250 1.3748 0.04342 0.03640 -0.0766 0.0217 1.0000
10.500 1.3857 0.04767 0.04099 -0.0751 0.0215 1.0000
10.750 1.3871 0.04927 0.04292 -0.0721 0.0211 1.0000
11.000 1.3842 0.05134 0.04527 -0.0688 0.0208 1.0000
11.250 1.3786 0.05388 0.04809 -0.0657 0.0205 1.0000
11.500 1.3705 0.05709 0.05159 -0.0631 0.0205 1.0000
11.750 1.3595 0.06097 0.05575 -0.0610 0.0206 1.0000
12.000 1.3459 0.06531 0.06036 -0.0595 0.0207 1.0000
12.250 1.3300 0.07008 0.06538 -0.0587 0.0209 1.0000
12.500 1.3126 0.07574 0.07127 -0.0588 0.0211 1.0000
13.500 1.1018 0.09949 0.09615 -0.0606 0.0218 1.0000
13.750 1.0700 0.10682 0.10369 -0.0651 0.0217 1.0000
14.000 1.0525 0.11272 0.10979 -0.0694 0.0222 1.0000
14.250 0.9413 0.14151 0.13916 -0.0912 0.0271 1.0000
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