FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 200,000 Max Cl/Cd: 55.99 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs02196-il-200000-n5.txt Download as CSV file: xf-fxs02196-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5031 0.08969 0.08557 -0.0766 1.0000 0.0174
-15.000 -0.5415 0.07921 0.07484 -0.0831 1.0000 0.0173
-14.750 -0.5681 0.07196 0.06738 -0.0872 1.0000 0.0173
-14.500 -0.5885 0.06516 0.06033 -0.0917 0.9762 0.0175
-14.250 -0.5970 0.05825 0.05298 -0.0997 0.9388 0.0179
-14.000 -0.6057 0.05188 0.04602 -0.1073 0.9128 0.0183
-13.750 -0.5910 0.04881 0.04280 -0.1108 0.8903 0.0188
-13.500 -0.5792 0.04651 0.04033 -0.1126 0.8688 0.0192
-13.250 -0.5712 0.04441 0.03807 -0.1137 0.8498 0.0199
-13.000 -0.5674 0.04217 0.03555 -0.1144 0.8334 0.0204
-12.750 -0.5679 0.03988 0.03293 -0.1143 0.8177 0.0210
-12.500 -0.5544 0.03860 0.03160 -0.1139 0.8043 0.0214
-12.250 -0.5438 0.03741 0.03035 -0.1135 0.7918 0.0219
-12.000 -0.5338 0.03612 0.02893 -0.1130 0.7797 0.0224
-11.750 -0.5224 0.03490 0.02755 -0.1125 0.7690 0.0229
-11.500 -0.5108 0.03366 0.02613 -0.1117 0.7579 0.0234
-11.250 -0.4982 0.03266 0.02506 -0.1111 0.7482 0.0239
-11.000 -0.4856 0.03176 0.02410 -0.1104 0.7385 0.0243
-10.750 -0.4736 0.03092 0.02317 -0.1098 0.7299 0.0248
-10.500 -0.4601 0.03006 0.02222 -0.1091 0.7211 0.0253
-10.250 -0.4463 0.02924 0.02126 -0.1083 0.7132 0.0260
-10.000 -0.4330 0.02849 0.02045 -0.1077 0.7055 0.0267
-9.750 -0.4180 0.02777 0.01965 -0.1069 0.6976 0.0271
-9.500 -0.4024 0.02706 0.01884 -0.1060 0.6907 0.0275
-9.250 -0.3871 0.02636 0.01807 -0.1052 0.6837 0.0282
-9.000 -0.3709 0.02565 0.01727 -0.1041 0.6769 0.0286
-8.750 -0.3558 0.02494 0.01646 -0.1030 0.6710 0.0288
-8.500 -0.3417 0.02423 0.01570 -0.1018 0.6653 0.0290
-8.250 -0.3299 0.02356 0.01497 -0.1003 0.6595 0.0292
-8.000 -0.3194 0.02295 0.01429 -0.0986 0.6544 0.0294
-7.750 -0.3056 0.02233 0.01360 -0.0975 0.6499 0.0297
-7.500 -0.2900 0.02173 0.01296 -0.0966 0.6452 0.0300
-7.250 -0.2733 0.02116 0.01234 -0.0957 0.6404 0.0305
-7.000 -0.2556 0.02062 0.01172 -0.0949 0.6359 0.0309
-6.750 -0.2367 0.02012 0.01113 -0.0943 0.6319 0.0315
-6.500 -0.2165 0.01966 0.01057 -0.0938 0.6284 0.0322
-6.250 -0.1950 0.01922 0.01007 -0.0934 0.6245 0.0329
-6.000 -0.1729 0.01878 0.00957 -0.0932 0.6207 0.0338
-5.750 -0.1496 0.01842 0.00912 -0.0930 0.6171 0.0352
-5.500 -0.1256 0.01809 0.00870 -0.0929 0.6138 0.0368
-5.250 -0.1014 0.01773 0.00824 -0.0929 0.6108 0.0385
-5.000 -0.0761 0.01746 0.00785 -0.0929 0.6079 0.0403
-4.750 -0.0509 0.01711 0.00747 -0.0930 0.6046 0.0420
-4.500 -0.0250 0.01683 0.00716 -0.0932 0.6012 0.0443
-4.250 0.0013 0.01658 0.00690 -0.0933 0.5976 0.0465
-4.000 0.0278 0.01632 0.00666 -0.0936 0.5941 0.0502
-3.750 0.0553 0.01624 0.00647 -0.0938 0.5908 0.0623
-3.500 0.0829 0.01617 0.00629 -0.0940 0.5876 0.0668
-3.250 0.1104 0.01607 0.00616 -0.0942 0.5844 0.0693
-3.000 0.1379 0.01592 0.00603 -0.0945 0.5807 0.0733
-2.750 0.1649 0.01566 0.00583 -0.0948 0.5759 0.0913
-2.500 0.1925 0.01563 0.00568 -0.0949 0.5704 0.1007
-2.250 0.2201 0.01558 0.00555 -0.0951 0.5649 0.1051
-2.000 0.2473 0.01544 0.00544 -0.0953 0.5586 0.1108
-1.750 0.2747 0.01526 0.00527 -0.0956 0.5524 0.1426
-1.500 0.3023 0.01508 0.00509 -0.0959 0.5477 0.1629
-1.250 0.3302 0.01473 0.00493 -0.0966 0.5438 0.2227
-0.750 0.3865 0.01395 0.00494 -0.0982 0.5364 0.4520
-0.500 0.4147 0.01400 0.00503 -0.0984 0.5333 0.4729
-0.250 0.4430 0.01407 0.00506 -0.0987 0.5301 0.4856
0.000 0.4711 0.01415 0.00509 -0.0989 0.5271 0.4948
0.250 0.4994 0.01422 0.00513 -0.0992 0.5240 0.5023
0.500 0.5268 0.01427 0.00527 -0.0993 0.5190 0.5126
0.750 0.5541 0.01434 0.00538 -0.0993 0.5133 0.5258
1.000 0.5810 0.01444 0.00543 -0.0993 0.5073 0.5371
1.250 0.6082 0.01450 0.00551 -0.0994 0.5018 0.5425
1.500 0.6354 0.01457 0.00561 -0.0995 0.4973 0.5463
1.750 0.6627 0.01466 0.00569 -0.0996 0.4936 0.5508
2.000 0.6899 0.01476 0.00576 -0.0997 0.4898 0.5575
2.250 0.7160 0.01487 0.00589 -0.0995 0.4852 0.5658
2.500 0.7424 0.01499 0.00606 -0.0995 0.4787 0.5762
2.750 0.7674 0.01511 0.00619 -0.0992 0.4703 0.5838
3.000 0.7924 0.01524 0.00635 -0.0989 0.4624 0.5909
3.250 0.8182 0.01536 0.00650 -0.0988 0.4528 0.5962
3.500 0.8433 0.01549 0.00663 -0.0986 0.4430 0.6003
3.750 0.8672 0.01562 0.00678 -0.0981 0.4290 0.6038
4.000 0.8874 0.01585 0.00693 -0.0971 0.4076 0.6074
4.250 0.8950 0.01652 0.00728 -0.0941 0.3526 0.6107
4.500 0.9033 0.01725 0.00784 -0.0914 0.3131 0.6142
4.750 0.9075 0.01801 0.00846 -0.0881 0.2901 0.6177
5.000 0.9165 0.01857 0.00900 -0.0855 0.2759 0.6209
5.500 0.9221 0.02046 0.01079 -0.0792 0.2289 0.6277
5.750 0.9304 0.02130 0.01163 -0.0772 0.2207 0.6318
6.000 0.9458 0.02188 0.01226 -0.0760 0.2140 0.6365
6.250 0.9531 0.02288 0.01328 -0.0741 0.1897 0.6407
6.500 0.9586 0.02404 0.01446 -0.0722 0.1839 0.6448
6.750 0.9642 0.02529 0.01573 -0.0704 0.1770 0.6495
7.000 0.9748 0.02632 0.01681 -0.0693 0.1728 0.6550
7.250 0.9830 0.02756 0.01810 -0.0680 0.1673 0.6605
7.500 0.9954 0.02854 0.01918 -0.0671 0.1602 0.6663
7.750 0.9988 0.03022 0.02087 -0.0656 0.1394 0.6728
8.000 1.0040 0.03185 0.02251 -0.0645 0.1354 0.6800
8.250 1.0105 0.03338 0.02410 -0.0634 0.1317 0.6871
8.500 1.0187 0.03485 0.02565 -0.0626 0.1279 0.6958
8.750 1.0260 0.03643 0.02729 -0.0617 0.1239 0.7044
9.000 1.0349 0.03791 0.02887 -0.0610 0.1201 0.7145
9.250 1.0494 0.03895 0.03005 -0.0606 0.1019 0.7259
9.500 1.0485 0.04132 0.03241 -0.0595 0.0953 0.7382
9.750 1.0541 0.04318 0.03432 -0.0588 0.0923 0.7523
10.000 1.0614 0.04490 0.03612 -0.0582 0.0901 0.7694
10.250 1.0679 0.04668 0.03800 -0.0575 0.0878 0.7911
10.500 1.0761 0.04820 0.03967 -0.0567 0.0862 0.8206
11.000 1.0908 0.05085 0.04267 -0.0547 0.0827 1.0000
11.250 1.1015 0.05258 0.04445 -0.0546 0.0804 1.0000
11.500 1.1138 0.05416 0.04610 -0.0546 0.0780 1.0000
11.750 1.1292 0.05546 0.04752 -0.0547 0.0659 1.0000
12.000 1.1327 0.05797 0.04999 -0.0546 0.0631 1.0000
12.250 1.1391 0.06023 0.05222 -0.0546 0.0605 1.0000
12.500 1.1453 0.06254 0.05453 -0.0546 0.0586 1.0000
12.750 1.1521 0.06482 0.05684 -0.0547 0.0571 1.0000
13.000 1.1592 0.06710 0.05916 -0.0548 0.0559 1.0000
13.250 1.1665 0.06938 0.06150 -0.0549 0.0548 1.0000
13.500 1.1747 0.07161 0.06381 -0.0551 0.0535 1.0000
13.750 1.1817 0.07398 0.06626 -0.0554 0.0522 1.0000
14.000 1.1869 0.07663 0.06898 -0.0557 0.0508 1.0000
14.250 1.1927 0.07923 0.07165 -0.0560 0.0495 1.0000
14.500 1.2024 0.08135 0.07388 -0.0563 0.0479 1.0000
14.750 1.2107 0.08367 0.07630 -0.0567 0.0460 1.0000
15.000 1.2180 0.08613 0.07885 -0.0571 0.0445 1.0000
15.250 1.2269 0.08840 0.08122 -0.0576 0.0425 1.0000
15.500 1.2351 0.09078 0.08369 -0.0581 0.0405 1.0000
15.750 1.2426 0.09325 0.08622 -0.0586 0.0393 1.0000
16.000 1.2494 0.09583 0.08886 -0.0592 0.0383 1.0000
16.250 1.2553 0.09857 0.09165 -0.0599 0.0376 1.0000
16.500 1.2615 0.10127 0.09440 -0.0607 0.0369 1.0000
16.750 1.2673 0.10403 0.09720 -0.0614 0.0362 1.0000
17.000 1.2718 0.10703 0.10025 -0.0623 0.0357 1.0000
17.250 1.2760 0.11005 0.10334 -0.0632 0.0352 1.0000
17.500 1.2804 0.11304 0.10640 -0.0642 0.0348 1.0000
17.750 1.2842 0.11613 0.10957 -0.0652 0.0345 1.0000
18.000 1.2880 0.11923 0.11273 -0.0663 0.0341 1.0000
18.250 1.2920 0.12227 0.11582 -0.0674 0.0337 1.0000
18.500 1.2958 0.12534 0.11895 -0.0686 0.0334 1.0000
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Polar graphs
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