FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 100,000 Max Cl/Cd: 37.48 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs02196-il-100000-n5.txt Download as CSV file: xf-fxs02196-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX S 02-196 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.3198 0.11434 0.10950 -0.0666 1.0000 0.0317
-13.500 -0.3480 0.09947 0.09462 -0.0751 0.9794 0.0318
-13.000 -0.4645 0.06815 0.06258 -0.0994 0.9397 0.0296
-12.750 -0.4609 0.06358 0.05780 -0.1052 0.9192 0.0304
-12.250 -0.4777 0.05440 0.04793 -0.1130 0.8791 0.0314
-12.000 -0.4913 0.05087 0.04401 -0.1142 0.8601 0.0321
-11.750 -0.5073 0.04779 0.04048 -0.1142 0.8430 0.0327
-11.500 -0.4974 0.04646 0.03910 -0.1140 0.8294 0.0337
-11.250 -0.4984 0.04465 0.03704 -0.1132 0.8165 0.0349
-11.000 -0.5033 0.04264 0.03470 -0.1118 0.8039 0.0356
-10.750 -0.5096 0.04090 0.03251 -0.1095 0.7935 0.0363
-10.500 -0.4921 0.03946 0.03105 -0.1090 0.7834 0.0371
-10.250 -0.4782 0.03810 0.02949 -0.1081 0.7750 0.0381
-10.000 -0.4628 0.03663 0.02780 -0.1073 0.7660 0.0388
-9.750 -0.4420 0.03519 0.02612 -0.1068 0.7579 0.0393
-9.500 -0.4179 0.03390 0.02458 -0.1064 0.7511 0.0398
-9.250 -0.3901 0.03276 0.02333 -0.1064 0.7432 0.0403
-9.000 -0.3600 0.03178 0.02234 -0.1064 0.7366 0.0410
-8.750 -0.3342 0.03099 0.02149 -0.1059 0.7308 0.0416
-8.500 -0.3122 0.03030 0.02077 -0.1051 0.7236 0.0424
-8.250 -0.2927 0.02964 0.02005 -0.1040 0.7172 0.0431
-8.000 -0.2760 0.02901 0.01932 -0.1028 0.7120 0.0441
-7.750 -0.2648 0.02836 0.01872 -0.1012 0.7053 0.0450
-7.500 -0.2539 0.02773 0.01807 -0.0997 0.6989 0.0461
-7.250 -0.2410 0.02708 0.01733 -0.0984 0.6937 0.0473
-7.000 -0.2277 0.02646 0.01664 -0.0971 0.6889 0.0484
-6.750 -0.2139 0.02589 0.01607 -0.0960 0.6833 0.0496
-6.500 -0.1984 0.02535 0.01547 -0.0950 0.6784 0.0511
-6.250 -0.1813 0.02482 0.01486 -0.0942 0.6743 0.0532
-6.000 -0.1625 0.02432 0.01421 -0.0935 0.6708 0.0567
-5.750 -0.1435 0.02390 0.01369 -0.0928 0.6665 0.0621
-5.500 -0.1244 0.02344 0.01315 -0.0923 0.6621 0.0689
-5.250 -0.1059 0.02279 0.01256 -0.0919 0.6581 0.0777
-5.000 -0.0849 0.02224 0.01201 -0.0917 0.6546 0.1059
-4.750 -0.0644 0.02141 0.01134 -0.0918 0.6516 0.1535
-4.500 -0.0455 0.02007 0.01050 -0.0924 0.6490 0.2666
-4.250 -0.0256 0.01983 0.01108 -0.0917 0.6452 0.3974
-4.000 0.0012 0.01988 0.01103 -0.0919 0.6415 0.4467
-3.750 0.0281 0.02004 0.01112 -0.0919 0.6380 0.4663
-3.500 0.0562 0.02009 0.01098 -0.0923 0.6348 0.4820
-3.250 0.0843 0.02020 0.01096 -0.0925 0.6320 0.4941
-3.000 0.1129 0.02031 0.01093 -0.0927 0.6297 0.5060
-2.750 0.1396 0.02053 0.01109 -0.0928 0.6269 0.5176
-2.500 0.1648 0.02085 0.01143 -0.0924 0.6239 0.5278
-2.250 0.1915 0.02110 0.01158 -0.0926 0.6210 0.5399
-2.000 0.2169 0.02138 0.01189 -0.0921 0.6182 0.5472
-1.750 0.2443 0.02151 0.01194 -0.0923 0.6155 0.5540
-1.500 0.2728 0.02158 0.01187 -0.0928 0.6131 0.5603
-1.250 0.2999 0.02175 0.01202 -0.0926 0.6110 0.5653
-1.000 0.3281 0.02198 0.01218 -0.0927 0.6092 0.5756
-0.750 0.3528 0.02238 0.01263 -0.0920 0.6073 0.5863
-0.500 0.3759 0.02283 0.01312 -0.0916 0.6047 0.5977
-0.250 0.3981 0.02323 0.01361 -0.0908 0.6021 0.6043
0.000 0.4217 0.02356 0.01397 -0.0904 0.5997 0.6098
0.250 0.4473 0.02381 0.01419 -0.0906 0.5974 0.6162
0.500 0.4733 0.02399 0.01435 -0.0906 0.5949 0.6213
0.750 0.4993 0.02411 0.01447 -0.0904 0.5925 0.6250
1.000 0.5283 0.02412 0.01443 -0.0908 0.5902 0.6280
1.250 0.5592 0.02407 0.01430 -0.0916 0.5881 0.6306
1.500 0.5810 0.02440 0.01467 -0.0913 0.5846 0.6333
1.750 0.6009 0.02478 0.01509 -0.0908 0.5802 0.6363
2.000 0.6257 0.02495 0.01525 -0.0910 0.5763 0.6394
2.250 0.6520 0.02496 0.01527 -0.0909 0.5729 0.6416
2.500 0.6810 0.02491 0.01521 -0.0912 0.5702 0.6442
2.750 0.7130 0.02477 0.01501 -0.0919 0.5677 0.6471
3.000 0.7302 0.02522 0.01556 -0.0908 0.5634 0.6502
3.250 0.7470 0.02563 0.01606 -0.0897 0.5581 0.6537
3.500 0.7748 0.02546 0.01586 -0.0898 0.5528 0.6576
3.750 0.8118 0.02485 0.01514 -0.0910 0.5481 0.6612
4.000 0.8296 0.02509 0.01548 -0.0897 0.5426 0.6644
4.250 0.8439 0.02548 0.01600 -0.0881 0.5366 0.6681
4.500 0.8692 0.02544 0.01597 -0.0879 0.5319 0.6726
4.750 0.9027 0.02511 0.01559 -0.0888 0.5279 0.6776
5.000 0.9214 0.02536 0.01592 -0.0877 0.5230 0.6821
5.250 0.9267 0.02606 0.01680 -0.0849 0.5170 0.6866
5.500 0.9456 0.02624 0.01704 -0.0839 0.5119 0.6921
5.750 0.9755 0.02603 0.01683 -0.0842 0.5078 0.6988
6.000 0.9876 0.02646 0.01738 -0.0823 0.5031 0.7043
6.250 0.9769 0.02767 0.01878 -0.0775 0.4974 0.7101
6.500 0.9870 0.02828 0.01947 -0.0756 0.4924 0.7174
6.750 1.0154 0.02801 0.01923 -0.0756 0.4881 0.7246
7.000 1.0160 0.02917 0.02053 -0.0729 0.4835 0.7321
7.250 0.9788 0.03296 0.02451 -0.0678 0.4753 0.7403
7.500 0.9935 0.03352 0.02518 -0.0668 0.4703 0.7491
7.750 1.0237 0.03305 0.02478 -0.0668 0.4670 0.7603
8.000 0.9552 0.04046 0.03241 -0.0620 0.4494 0.7685
8.500 0.9383 0.04650 0.03875 -0.0592 0.4297 0.7951
8.750 0.9247 0.05019 0.04260 -0.0579 0.4178 0.8121
9.000 0.9368 0.05080 0.04338 -0.0566 0.4122 0.8416
9.250 0.9289 0.05327 0.04606 -0.0546 0.4020 0.8969
9.500 0.9364 0.05466 0.04754 -0.0541 0.3935 1.0000
9.750 0.9384 0.05738 0.05032 -0.0542 0.3823 1.0000
10.000 0.9539 0.05852 0.05149 -0.0543 0.3737 1.0000
10.250 0.9682 0.05976 0.05277 -0.0543 0.3639 1.0000
10.500 0.9990 0.05891 0.05189 -0.0542 0.3551 1.0000
10.750 1.0203 0.05920 0.05217 -0.0541 0.3430 1.0000
11.000 1.0425 0.05937 0.05232 -0.0539 0.3309 1.0000
11.250 1.0545 0.06081 0.05377 -0.0538 0.3137 1.0000
11.500 1.0818 0.06014 0.05293 -0.0534 0.2953 1.0000
11.750 1.0990 0.06072 0.05336 -0.0529 0.2792 1.0000
12.000 1.1041 0.06305 0.05571 -0.0528 0.2562 1.0000
12.500 1.1146 0.06727 0.05960 -0.0523 0.2211 1.0000
12.750 1.1210 0.06966 0.06207 -0.0524 0.1979 1.0000
13.000 1.1201 0.07270 0.06494 -0.0524 0.1822 1.0000
13.250 1.1222 0.07553 0.06770 -0.0525 0.1697 1.0000
13.500 1.1292 0.07793 0.07018 -0.0528 0.1482 1.0000
13.750 1.1260 0.08153 0.07359 -0.0531 0.1347 1.0000
14.000 1.1275 0.08463 0.07664 -0.0535 0.1252 1.0000
14.250 1.1361 0.08692 0.07908 -0.0538 0.1102 1.0000
14.500 1.1363 0.09029 0.08236 -0.0544 0.0974 1.0000
14.750 1.1367 0.09370 0.08568 -0.0550 0.0914 1.0000
15.000 1.1370 0.09715 0.08910 -0.0557 0.0866 1.0000
15.250 1.1427 0.09990 0.09197 -0.0563 0.0807 1.0000
15.500 1.1509 0.10233 0.09457 -0.0568 0.0739 1.0000
15.750 1.1567 0.10512 0.09744 -0.0575 0.0683 1.0000
16.000 1.1602 0.10823 0.10056 -0.0584 0.0651 1.0000
16.250 1.1635 0.11139 0.10371 -0.0593 0.0629 1.0000
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Polar graphs
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