FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 100,000 Max Cl/Cd: 5.74 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66196v-il-100000.txt Download as CSV file: xf-fx66196v-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 V1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1440 0.10743 0.10300 -0.0975 0.9143 0.1545
-11.500 -0.1271 0.10413 0.09957 -0.1007 0.8987 0.1646
-11.250 -0.1252 0.09967 0.09506 -0.1037 0.8846 0.1696
-11.000 -0.1082 0.09649 0.09177 -0.1045 0.8709 0.1730
-10.750 -0.1063 0.09269 0.08792 -0.1063 0.8592 0.1760
-10.500 -0.3921 0.05595 0.05035 -0.1293 0.8514 0.0676
-10.250 -0.3974 0.05401 0.04810 -0.1274 0.8398 0.0656
-10.000 -0.3970 0.05053 0.04439 -0.1263 0.8314 0.0645
-9.750 -0.4001 0.04787 0.04148 -0.1244 0.8209 0.0638
-9.500 -0.3991 0.04535 0.03863 -0.1226 0.8126 0.0633
-9.250 -0.3957 0.04318 0.03610 -0.1207 0.8042 0.0638
-9.000 -0.3882 0.04125 0.03377 -0.1190 0.7969 0.0646
-8.750 -0.3783 0.03967 0.03177 -0.1173 0.7894 0.0657
-8.500 -0.3618 0.03770 0.02937 -0.1161 0.7842 0.0665
-8.250 -0.3417 0.03518 0.02678 -0.1155 0.7769 0.0679
-8.000 -0.3181 0.03356 0.02510 -0.1151 0.7717 0.0711
-7.750 -0.2967 0.03252 0.02391 -0.1143 0.7661 0.0755
-7.500 -0.2757 0.03164 0.02278 -0.1133 0.7598 0.0791
-7.250 -0.2479 0.02992 0.02123 -0.1129 0.7555 0.0851
-7.000 -0.2279 0.02930 0.02050 -0.1118 0.7503 0.0930
-6.750 -0.2104 0.02841 0.01985 -0.1103 0.7447 0.1027
-6.500 -0.1943 0.02759 0.01912 -0.1086 0.7406 0.1174
-6.250 -0.1820 0.02661 0.01832 -0.1067 0.7373 0.1417
-6.000 -0.1827 0.02568 0.01787 -0.1042 0.7314 0.1892
-5.750 -0.1858 0.02472 0.01849 -0.1006 0.7271 0.4618
-5.500 -0.1606 0.02640 0.01993 -0.0985 0.7240 0.5221
-5.250 -0.1347 0.02828 0.02180 -0.0956 0.7211 0.5473
-5.000 -0.1212 0.02998 0.02351 -0.0925 0.7159 0.5655
-4.750 -0.1019 0.03132 0.02476 -0.0899 0.7123 0.5848
-4.500 -0.0783 0.03260 0.02595 -0.0871 0.7095 0.6024
-4.250 -0.0514 0.03387 0.02714 -0.0841 0.7074 0.6190
-4.000 -0.0425 0.03528 0.02857 -0.0803 0.7030 0.6322
-3.750 -0.0363 0.03680 0.03013 -0.0758 0.6986 0.6418
-3.500 -0.0255 0.03749 0.03075 -0.0733 0.6956 0.6540
-3.250 -0.0101 0.03773 0.03085 -0.0722 0.6934 0.6666
-3.000 0.0134 0.03818 0.03123 -0.0701 0.6918 0.6738
-2.750 -0.0145 0.03988 0.03296 -0.0666 0.6879 0.6822
-2.500 -0.1023 0.04368 0.03703 -0.0557 0.6840 0.6835
-2.250 -0.2597 0.05234 0.04618 -0.0512 0.8000 0.6631
-2.000 -0.2699 0.05198 0.04584 -0.0454 0.7922 0.6730
-1.750 -0.2544 0.05298 0.04679 -0.0427 0.7888 0.6892
-1.500 -0.2298 0.05404 0.04772 -0.0424 0.7865 0.7016
-1.250 -0.1984 0.05545 0.04898 -0.0437 0.7850 0.7091
-1.000 -0.2032 0.05456 0.04797 -0.0413 0.7769 0.7140
-0.750 -0.1789 0.05520 0.04852 -0.0413 0.7727 0.7181
-0.500 -0.1451 0.05646 0.04964 -0.0432 0.7702 0.7233
-0.250 -0.1422 0.05638 0.04946 -0.0417 0.7645 0.7274
0.000 -0.1188 0.05684 0.04978 -0.0428 0.7589 0.7307
0.250 -0.0908 0.05778 0.05063 -0.0438 0.7559 0.7337
0.500 -0.0549 0.05937 0.05211 -0.0462 0.7540 0.7368
0.750 -0.0599 0.05880 0.05150 -0.0434 0.7447 0.7396
1.000 -0.0295 0.05981 0.05237 -0.0453 0.7408 0.7433
1.250 0.0052 0.06133 0.05378 -0.0478 0.7387 0.7469
1.500 0.0019 0.06123 0.05367 -0.0450 0.7309 0.7496
1.750 0.0282 0.06212 0.05450 -0.0460 0.7259 0.7528
2.000 0.0629 0.06368 0.05597 -0.0482 0.7233 0.7563
2.250 0.0638 0.06394 0.05619 -0.0466 0.7160 0.7598
2.500 0.0893 0.06487 0.05706 -0.0476 0.7104 0.7634
2.750 0.1226 0.06646 0.05861 -0.0493 0.7077 0.7669
3.000 0.1593 0.06875 0.06086 -0.0517 0.7063 0.7710
3.250 0.1454 0.06783 0.05994 -0.0483 0.6951 0.7745
3.500 0.1788 0.06947 0.06153 -0.0502 0.6921 0.7790
3.750 0.2165 0.07190 0.06395 -0.0524 0.6906 0.7838
4.000 0.2006 0.07110 0.06318 -0.0489 0.6795 0.7882
4.250 0.2325 0.07280 0.06485 -0.0506 0.6766 0.7946
4.500 0.2693 0.07523 0.06730 -0.0527 0.6750 0.8008
4.750 0.2568 0.07470 0.06680 -0.0498 0.6635 0.8062
5.000 0.2890 0.07654 0.06864 -0.0514 0.6608 0.8132
5.250 0.3244 0.07917 0.07129 -0.0536 0.6591 0.8220
5.500 0.3125 0.07864 0.07081 -0.0508 0.6473 0.8286
5.750 0.3482 0.08075 0.07296 -0.0527 0.6447 0.8400
6.000 0.3400 0.08122 0.07350 -0.0506 0.6348 0.8491
6.250 0.3692 0.08277 0.07514 -0.0518 0.6305 0.8644
6.500 0.4065 0.08516 0.07764 -0.0538 0.6285 0.8869
6.750 0.3968 0.08532 0.07796 -0.0521 0.6171 0.9133
7.000 0.4381 0.08745 0.08019 -0.0560 0.6136 1.0000
7.250 0.4365 0.08886 0.08160 -0.0563 0.6042 1.0000
7.500 0.4722 0.09100 0.08369 -0.0594 0.5994 1.0000
7.750 0.5175 0.09422 0.08689 -0.0630 0.5972 1.0000
8.000 0.5037 0.09471 0.08738 -0.0614 0.5851 1.0000
8.250 0.5449 0.09745 0.09011 -0.0640 0.5822 1.0000
8.500 0.5336 0.09852 0.09120 -0.0627 0.5706 1.0000
8.750 0.5737 0.10093 0.09363 -0.0648 0.5669 1.0000
9.000 0.5630 0.10241 0.09514 -0.0637 0.5558 1.0000
9.250 0.6009 0.10460 0.09735 -0.0654 0.5516 1.0000
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