FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 50,000 Max Cl/Cd: 7.82 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66196v-il-50000-n5.txt Download as CSV file: xf-fx66196v-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2707 0.10855 0.10239 -0.0822 0.9493 0.0524
-12.250 -0.2735 0.10008 0.09389 -0.0890 0.9385 0.0521
-12.000 -0.2846 0.09082 0.08456 -0.0966 0.9278 0.0516
-11.750 -0.3043 0.08166 0.07526 -0.1045 0.9162 0.0510
-11.500 -0.3248 0.07387 0.06725 -0.1114 0.9035 0.0504
-11.250 -0.3433 0.06764 0.06073 -0.1166 0.8899 0.0501
-11.000 -0.3572 0.06293 0.05571 -0.1198 0.8761 0.0501
-10.750 -0.3693 0.05915 0.05161 -0.1215 0.8625 0.0506
-10.500 -0.3797 0.05618 0.04834 -0.1216 0.8490 0.0513
-10.250 -0.3890 0.05374 0.04559 -0.1207 0.8360 0.0521
-10.000 -0.3962 0.05167 0.04317 -0.1190 0.8247 0.0530
-9.750 -0.3949 0.04938 0.04041 -0.1178 0.8160 0.0542
-9.500 -0.3840 0.04732 0.03815 -0.1167 0.8060 0.0555
-9.250 -0.3629 0.04541 0.03608 -0.1164 0.7989 0.0574
-9.000 -0.3460 0.04401 0.03452 -0.1155 0.7902 0.0603
-8.750 -0.3234 0.04250 0.03265 -0.1149 0.7838 0.0646
-8.500 -0.2915 0.04125 0.03131 -0.1145 0.7763 0.0690
-8.250 -0.2611 0.04020 0.03013 -0.1140 0.7706 0.0748
-8.000 -0.2409 0.03943 0.02926 -0.1126 0.7635 0.0815
-7.750 -0.2259 0.03865 0.02844 -0.1109 0.7571 0.0887
-7.500 -0.2157 0.03782 0.02758 -0.1090 0.7514 0.0971
-7.250 -0.2093 0.03715 0.02686 -0.1069 0.7443 0.1066
-7.000 -0.2037 0.03609 0.02587 -0.1050 0.7392 0.1190
-6.750 -0.2033 0.03522 0.02511 -0.1027 0.7329 0.1346
-6.500 -0.2050 0.03408 0.02420 -0.1003 0.7270 0.1577
-6.250 -0.2059 0.03249 0.02296 -0.0983 0.7227 0.2037
-6.000 -0.2122 0.03156 0.02279 -0.0950 0.7162 0.2867
-5.750 -0.1951 0.03320 0.02511 -0.0905 0.7115 0.4318
-5.500 -0.1792 0.03362 0.02516 -0.0892 0.7079 0.4865
-5.250 -0.1637 0.03483 0.02618 -0.0865 0.7033 0.5192
-5.000 -0.1477 0.03641 0.02767 -0.0829 0.6982 0.5451
-4.750 -0.1290 0.03740 0.02844 -0.0802 0.6944 0.5708
-4.500 -0.1024 0.03841 0.02925 -0.0776 0.6917 0.5893
-4.250 -0.0925 0.03898 0.02970 -0.0749 0.6868 0.6034
-4.000 -0.0796 0.03954 0.03013 -0.0724 0.6820 0.6141
-3.750 -0.0605 0.03971 0.03012 -0.0710 0.6787 0.6236
-3.500 -0.0411 0.03945 0.02961 -0.0706 0.6762 0.6344
-3.250 -0.0275 0.03990 0.02995 -0.0685 0.6728 0.6402
-3.000 -0.0283 0.04038 0.03036 -0.0662 0.6676 0.6480
-2.750 -0.0136 0.04060 0.03044 -0.0649 0.6644 0.6534
-2.500 0.0070 0.04064 0.03031 -0.0644 0.6620 0.6593
-2.250 0.0313 0.04039 0.02983 -0.0651 0.6600 0.6665
-2.000 0.0201 0.04164 0.03113 -0.0610 0.6537 0.6703
-1.750 0.0292 0.04216 0.03156 -0.0596 0.6499 0.6750
-1.500 0.0487 0.04232 0.03154 -0.0599 0.6473 0.6802
-1.250 0.0711 0.04248 0.03156 -0.0601 0.6455 0.6843
-1.000 0.0957 0.04262 0.03156 -0.0602 0.6440 0.6880
-0.750 0.0616 0.04505 0.03410 -0.0551 0.6371 0.6923
-0.500 0.0760 0.04571 0.03462 -0.0551 0.6338 0.6973
-0.250 0.0955 0.04615 0.03496 -0.0549 0.6315 0.7008
0.000 0.1190 0.04650 0.03521 -0.0551 0.6297 0.7044
0.250 0.1440 0.04689 0.03547 -0.0558 0.6283 0.7085
0.500 0.1337 0.04901 0.03757 -0.0540 0.6235 0.7131
0.750 0.1433 0.05009 0.03862 -0.0532 0.6201 0.7166
1.000 0.1607 0.05088 0.03934 -0.0532 0.6176 0.7201
1.250 0.1822 0.05158 0.03995 -0.0536 0.6156 0.7239
1.500 0.2083 0.05215 0.04041 -0.0546 0.6138 0.7285
1.750 0.2300 0.05283 0.04104 -0.0548 0.6117 0.7327
2.000 0.2244 0.05473 0.04297 -0.0530 0.6072 0.7370
2.250 0.2373 0.05592 0.04412 -0.0529 0.6045 0.7419
2.500 0.2570 0.05683 0.04498 -0.0533 0.6018 0.7469
2.750 0.2796 0.05752 0.04565 -0.0535 0.5995 0.7514
3.000 0.3059 0.05817 0.04627 -0.0542 0.5977 0.7567
3.250 0.3120 0.05982 0.04791 -0.0538 0.5945 0.7624
3.500 0.3170 0.06130 0.04945 -0.0528 0.5906 0.7677
3.750 0.3335 0.06239 0.05054 -0.0529 0.5874 0.7746
4.000 0.3549 0.06326 0.05144 -0.0530 0.5847 0.7818
4.250 0.3796 0.06406 0.05225 -0.0535 0.5827 0.7900
4.500 0.3865 0.06556 0.05380 -0.0528 0.5787 0.7979
4.750 0.3937 0.06700 0.05531 -0.0521 0.5739 0.8071
5.000 0.4115 0.06798 0.05635 -0.0520 0.5705 0.8170
5.250 0.4353 0.06875 0.05720 -0.0522 0.5679 0.8294
5.500 0.4530 0.06977 0.05830 -0.0520 0.5646 0.8441
5.750 0.4519 0.07155 0.06021 -0.0508 0.5590 0.8616
6.000 0.4704 0.07253 0.06132 -0.0510 0.5550 0.8891
6.250 0.4993 0.07310 0.06205 -0.0525 0.5518 0.9897
6.500 0.5090 0.07504 0.06397 -0.0530 0.5470 1.0000
6.750 0.5216 0.07687 0.06581 -0.0539 0.5417 1.0000
7.000 0.5475 0.07813 0.06706 -0.0552 0.5379 1.0000
7.250 0.5790 0.07916 0.06809 -0.0566 0.5354 1.0000
7.500 0.5736 0.08164 0.07060 -0.0562 0.5273 1.0000
7.750 0.5977 0.08286 0.07182 -0.0570 0.5229 1.0000
8.000 0.6294 0.08375 0.07275 -0.0580 0.5201 1.0000
8.250 0.6228 0.08628 0.07533 -0.0574 0.5110 1.0000
8.500 0.6482 0.08738 0.07647 -0.0581 0.5069 1.0000
8.750 0.6570 0.08931 0.07845 -0.0581 0.5005 1.0000
9.000 0.6700 0.09100 0.08022 -0.0582 0.4941 1.0000
9.250 0.6968 0.09203 0.08133 -0.0588 0.4906 1.0000
9.750 0.7189 0.09556 0.08501 -0.0589 0.4769 1.0000
10.000 0.7270 0.09751 0.08704 -0.0589 0.4697 1.0000
10.250 0.7438 0.09889 0.08854 -0.0590 0.4631 1.0000
10.500 0.7729 0.09958 0.08933 -0.0595 0.4595 1.0000
10.750 0.7690 0.10221 0.09206 -0.0592 0.4490 1.0000
11.000 0.7987 0.10275 0.09274 -0.0595 0.4453 1.0000
11.250 0.7943 0.10552 0.09561 -0.0594 0.4346 1.0000
11.500 0.8235 0.10594 0.09617 -0.0596 0.4305 1.0000
11.750 0.8205 0.10870 0.09904 -0.0596 0.4197 1.0000
12.000 0.8511 0.10879 0.09928 -0.0597 0.4157 1.0000
12.250 0.8496 0.11142 0.10205 -0.0597 0.4045 1.0000
12.500 0.8560 0.11345 0.10422 -0.0598 0.3950 1.0000
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