FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il) Reynolds number: 50,000 Max Cl/Cd: 38.27 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601001-il-50000.txt Download as CSV file: xf-fx601001-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3610 0.10517 0.09839 -0.0227 1.0000 0.2671
-8.250 -0.3468 0.10088 0.09411 -0.0219 1.0000 0.2749
-8.000 -0.3580 0.09956 0.09294 -0.0217 1.0000 0.2841
-7.750 -0.3588 0.09754 0.09098 -0.0206 1.0000 0.2967
-7.500 -0.3500 0.09429 0.08778 -0.0193 1.0000 0.3103
-7.250 -0.3415 0.09106 0.08459 -0.0179 1.0000 0.3229
-7.000 -0.3372 0.08814 0.08175 -0.0166 1.0000 0.3331
-6.750 -0.3480 0.08663 0.08039 -0.0147 1.0000 0.3426
-6.500 -0.3437 0.08375 0.07757 -0.0131 1.0000 0.3490
-6.250 -0.4260 0.06819 0.06230 -0.0452 1.0000 0.1667
-6.000 -0.4191 0.05818 0.05206 -0.0546 1.0000 0.1355
-5.750 -0.4012 0.04929 0.04256 -0.0643 1.0000 0.1215
-5.500 -0.3783 0.04386 0.03666 -0.0686 1.0000 0.1190
-5.250 -0.3497 0.03903 0.03116 -0.0727 1.0000 0.1202
-5.000 -0.3183 0.03494 0.02636 -0.0756 1.0000 0.1218
-4.750 -0.2867 0.03160 0.02232 -0.0773 1.0000 0.1254
-4.500 -0.2592 0.02942 0.01980 -0.0778 1.0000 0.1388
-4.250 -0.2335 0.02724 0.01763 -0.0777 1.0000 0.1557
-4.000 -0.2076 0.02555 0.01600 -0.0776 1.0000 0.1859
-3.750 -0.1810 0.02404 0.01457 -0.0776 1.0000 0.2262
-3.500 -0.1533 0.02241 0.01331 -0.0778 1.0000 0.2852
-3.250 -0.1357 0.02254 0.01464 -0.0744 1.0000 0.4299
-3.000 -0.1277 0.02390 0.01609 -0.0685 1.0000 0.5308
-2.750 -0.1188 0.02448 0.01665 -0.0636 1.0000 0.5834
-2.500 -0.1108 0.02477 0.01694 -0.0588 1.0000 0.6195
-2.250 -0.1020 0.02497 0.01710 -0.0545 1.0000 0.6581
-2.000 -0.0969 0.02510 0.01720 -0.0494 1.0000 0.6996
-1.750 -0.0935 0.02494 0.01707 -0.0441 1.0000 0.7362
-1.500 -0.0820 0.02468 0.01671 -0.0413 1.0000 0.7696
-1.250 -0.0679 0.02437 0.01628 -0.0395 1.0000 0.7946
-1.000 -0.0507 0.02414 0.01593 -0.0386 1.0000 0.8171
-0.750 -0.0330 0.02400 0.01568 -0.0380 1.0000 0.8380
-0.500 -0.0146 0.02394 0.01550 -0.0377 1.0000 0.8584
-0.250 0.0027 0.02392 0.01542 -0.0372 1.0000 0.8797
0.000 0.0207 0.02394 0.01543 -0.0369 1.0000 0.9062
0.250 0.0433 0.02396 0.01548 -0.0383 1.0000 0.9530
0.500 0.0734 0.02443 0.01582 -0.0421 0.9974 1.0000
0.750 0.1322 0.02574 0.01691 -0.0507 0.9852 1.0000
1.000 0.1872 0.02694 0.01793 -0.0584 0.9725 1.0000
1.250 0.2399 0.02808 0.01892 -0.0653 0.9589 1.0000
1.500 0.2910 0.02915 0.01988 -0.0718 0.9447 1.0000
1.750 0.3411 0.03017 0.02081 -0.0777 0.9299 1.0000
2.000 0.3899 0.03112 0.02170 -0.0831 0.9148 1.0000
2.250 0.4373 0.03200 0.02255 -0.0881 0.8997 1.0000
2.500 0.4849 0.03281 0.02336 -0.0927 0.8842 1.0000
2.750 0.5293 0.03354 0.02409 -0.0965 0.8680 1.0000
3.000 0.5659 0.03426 0.02483 -0.0990 0.8503 1.0000
3.250 0.6069 0.03485 0.02550 -0.1016 0.8322 1.0000
3.500 0.6545 0.03515 0.02588 -0.1047 0.8141 1.0000
3.750 0.7026 0.03517 0.02606 -0.1072 0.7948 1.0000
4.000 0.7445 0.03510 0.02612 -0.1084 0.7729 1.0000
4.250 0.8057 0.03387 0.02510 -0.1108 0.7540 1.0000
4.500 0.8387 0.03371 0.02513 -0.1102 0.7305 1.0000
4.750 0.8910 0.03232 0.02394 -0.1107 0.7109 1.0000
5.000 0.9232 0.03198 0.02378 -0.1095 0.6859 1.0000
5.250 0.9606 0.03125 0.02325 -0.1084 0.6610 1.0000
5.500 0.9984 0.03043 0.02257 -0.1071 0.6347 1.0000
5.750 1.0309 0.03003 0.02228 -0.1055 0.6052 1.0000
6.250 1.0888 0.03001 0.02242 -0.1018 0.5415 1.0000
6.500 1.1171 0.03003 0.02242 -0.0999 0.5088 1.0000
6.750 1.1401 0.03044 0.02287 -0.0979 0.4755 1.0000
7.000 1.1624 0.03088 0.02337 -0.0958 0.4427 1.0000
7.250 1.1861 0.03103 0.02346 -0.0937 0.4082 1.0000
7.500 1.2031 0.03144 0.02377 -0.0909 0.3675 1.0000
7.750 1.2130 0.03190 0.02395 -0.0875 0.3178 1.0000
8.000 1.2152 0.03294 0.02467 -0.0835 0.2628 1.0000
8.250 1.2106 0.03517 0.02654 -0.0791 0.1988 1.0000
8.500 1.2116 0.03824 0.02907 -0.0755 0.1474 1.0000
8.750 1.2285 0.04128 0.03193 -0.0736 0.1201 1.0000
9.000 1.2489 0.04411 0.03479 -0.0723 0.1046 1.0000
9.250 1.2710 0.04728 0.03808 -0.0714 0.0946 1.0000
9.500 1.2938 0.05092 0.04199 -0.0705 0.0890 1.0000
9.750 1.3155 0.05546 0.04665 -0.0699 0.0854 1.0000
10.000 1.3187 0.05952 0.05136 -0.0675 0.0837 1.0000
10.250 1.3164 0.06375 0.05612 -0.0651 0.0823 1.0000
10.500 1.3087 0.06805 0.06088 -0.0627 0.0813 1.0000
10.750 1.2952 0.07239 0.06560 -0.0603 0.0810 1.0000
11.000 1.2758 0.07669 0.07020 -0.0579 0.0813 1.0000
11.250 1.2534 0.08142 0.07520 -0.0565 0.0818 1.0000
11.500 1.2296 0.08677 0.08078 -0.0564 0.0826 1.0000
11.750 1.2057 0.09281 0.08700 -0.0577 0.0835 1.0000
12.000 1.1833 0.09948 0.09381 -0.0600 0.0844 1.0000
12.250 1.1643 0.10660 0.10103 -0.0629 0.0853 1.0000
12.500 1.0764 0.12816 0.12270 -0.0806 0.0971 1.0000
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Polar data table (+)
Polar graphs
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