FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 50,000 Max Cl/Cd: 5.07 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61168-il-50000.txt Download as CSV file: xf-fx61168-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2908 0.10692 0.10095 -0.0297 1.0000 0.3520
-8.750 -0.4406 0.08774 0.08235 -0.0492 1.0000 0.1709
-8.500 -0.4710 0.08534 0.08012 -0.0463 1.0000 0.1595
-8.250 -0.5165 0.08511 0.08009 -0.0417 1.0000 0.1589
-8.000 -0.5568 0.08449 0.07960 -0.0377 1.0000 0.1597
-7.750 -0.5962 0.08257 0.07777 -0.0358 1.0000 0.1594
-7.500 -0.6378 0.07929 0.07443 -0.0353 1.0000 0.1573
-7.250 -0.6598 0.07496 0.06992 -0.0353 1.0000 0.1463
-7.000 -0.6803 0.06993 0.06446 -0.0361 1.0000 0.1343
-6.750 -0.6878 0.06484 0.05870 -0.0370 1.0000 0.1217
-6.500 -0.6681 0.05971 0.05243 -0.0410 0.9955 0.1088
-6.250 -0.6399 0.05537 0.04791 -0.0433 0.9899 0.1067
-6.000 -0.6091 0.05178 0.04377 -0.0461 0.9842 0.1058
-5.750 -0.5796 0.04885 0.04039 -0.0479 0.9785 0.1051
-5.500 -0.5452 0.04622 0.03730 -0.0498 0.9732 0.1042
-5.250 -0.5162 0.04418 0.03487 -0.0503 0.9675 0.1046
-5.000 -0.4787 0.04275 0.03293 -0.0520 0.9620 0.1086
-4.750 -0.4576 0.04126 0.03158 -0.0507 0.9567 0.1141
-4.500 -0.4300 0.04048 0.03071 -0.0496 0.9515 0.1205
-4.250 -0.4047 0.03988 0.03022 -0.0481 0.9467 0.1308
-4.000 -0.3879 0.03917 0.02961 -0.0461 0.9415 0.1450
-3.750 -0.3626 0.03800 0.02867 -0.0464 0.9363 0.1725
-3.500 -0.3539 0.03523 0.02894 -0.0439 0.9324 0.4808
-3.250 -0.3710 0.04064 0.03439 -0.0274 0.9279 0.6678
-3.000 -0.1804 0.05232 0.04496 -0.0195 0.9194 0.8691
-2.750 -0.1798 0.05187 0.04435 -0.0172 0.9138 0.8802
-2.500 -0.1686 0.05149 0.04379 -0.0167 0.9084 0.8916
-2.250 -0.1261 0.05102 0.04300 -0.0215 0.9026 0.9038
-2.000 -0.1042 0.05065 0.04245 -0.0229 0.8969 0.9139
-1.750 -0.0718 0.05040 0.04197 -0.0261 0.8912 0.9238
-1.500 -0.0596 0.05033 0.04176 -0.0260 0.8860 0.9324
-1.250 -0.0343 0.05021 0.04149 -0.0281 0.8804 0.9404
-1.000 0.0094 0.05021 0.04126 -0.0332 0.8742 0.9495
-0.750 0.0187 0.05032 0.04129 -0.0328 0.8685 0.9568
-0.500 0.0564 0.05045 0.04126 -0.0371 0.8621 0.9651
-0.250 0.0809 0.05076 0.04145 -0.0391 0.8560 0.9724
0.000 0.1075 0.05107 0.04167 -0.0418 0.8497 0.9787
0.250 0.1521 0.05149 0.04195 -0.0471 0.8430 0.9853
0.500 0.1603 0.05207 0.04250 -0.0469 0.8375 0.9905
0.750 0.1962 0.05264 0.04298 -0.0509 0.8309 0.9960
1.000 0.2137 0.05342 0.04370 -0.0521 0.8253 1.0000
1.250 0.2025 0.05420 0.04448 -0.0484 0.8222 1.0000
1.500 0.1974 0.05494 0.04521 -0.0456 0.8192 1.0000
1.750 0.1969 0.05571 0.04595 -0.0436 0.8165 1.0000
2.000 0.2061 0.05657 0.04677 -0.0428 0.8124 1.0000
2.250 0.1992 0.05749 0.04768 -0.0400 0.8130 1.0000
2.500 -0.0455 0.05494 0.04557 -0.0037 0.9745 1.0000
2.750 -0.0282 0.05570 0.04627 -0.0050 0.9629 1.0000
3.000 -0.0124 0.05643 0.04694 -0.0059 0.9503 1.0000
3.250 0.0021 0.05714 0.04761 -0.0065 0.9373 1.0000
3.500 0.0154 0.05785 0.04827 -0.0069 0.9240 1.0000
3.750 0.0296 0.05867 0.04904 -0.0073 0.9110 1.0000
4.000 0.0473 0.05981 0.05013 -0.0084 0.8991 1.0000
4.250 0.0736 0.06170 0.05198 -0.0111 0.8878 1.0000
4.500 0.1051 0.06390 0.05414 -0.0146 0.8745 1.0000
4.750 0.1253 0.06502 0.05525 -0.0162 0.8605 1.0000
5.000 0.1459 0.06636 0.05657 -0.0179 0.8470 1.0000
5.250 0.1682 0.06798 0.05820 -0.0199 0.8337 1.0000
5.500 0.1919 0.06986 0.06007 -0.0222 0.8213 1.0000
5.750 0.2199 0.07219 0.06241 -0.0252 0.8097 1.0000
6.000 0.2603 0.07555 0.06579 -0.0300 0.7977 1.0000
6.250 0.2781 0.07690 0.06717 -0.0313 0.7836 1.0000
6.500 0.2957 0.07853 0.06885 -0.0328 0.7701 1.0000
6.750 0.3146 0.08050 0.07086 -0.0345 0.7576 1.0000
7.000 0.3370 0.08283 0.07324 -0.0368 0.7453 1.0000
7.250 0.3661 0.08575 0.07622 -0.0398 0.7339 1.0000
7.500 0.4033 0.08923 0.07976 -0.0437 0.7206 1.0000
7.750 0.4195 0.09104 0.08164 -0.0450 0.7061 1.0000
8.000 0.4333 0.09293 0.08361 -0.0462 0.6923 1.0000
8.250 0.4480 0.09514 0.08591 -0.0475 0.6791 1.0000
8.500 0.4645 0.09770 0.08855 -0.0492 0.6670 1.0000
8.750 0.4866 0.10070 0.09163 -0.0514 0.6553 1.0000
9.000 0.5190 0.10440 0.09543 -0.0546 0.6430 1.0000
9.250 0.5417 0.10731 0.09847 -0.0566 0.6287 1.0000
9.500 0.5502 0.10937 0.10062 -0.0575 0.6147 1.0000
9.750 0.5579 0.11179 0.10313 -0.0585 0.6019 1.0000
10.000 0.5704 0.11468 0.10612 -0.0600 0.5898 1.0000
10.250 0.5916 0.11830 0.10986 -0.0622 0.5795 1.0000
10.500 0.6185 0.12204 0.11373 -0.0646 0.5662 1.0000
10.750 0.6305 0.12472 0.11651 -0.0659 0.5529 1.0000
11.000 0.6290 0.12721 0.11909 -0.0668 0.5425 1.0000
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Polar data table (+)
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