FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.12 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs02196-il-1000000.txt Download as CSV file: xf-fxs02196-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.7659 0.11323 0.11075 -0.0546 1.0000 0.0083
-19.250 -0.7977 0.10350 0.10085 -0.0600 1.0000 0.0083
-19.000 -0.8189 0.09597 0.09318 -0.0642 1.0000 0.0082
-18.750 -0.8346 0.08959 0.08669 -0.0677 1.0000 0.0082
-18.500 -0.8476 0.08387 0.08084 -0.0709 1.0000 0.0083
-18.250 -0.8579 0.07868 0.07554 -0.0737 1.0000 0.0083
-18.000 -0.8654 0.07411 0.07089 -0.0760 1.0000 0.0083
-17.750 -0.8640 0.07077 0.06749 -0.0779 1.0000 0.0084
-17.500 -0.8618 0.06764 0.06430 -0.0796 1.0000 0.0085
-17.250 -0.8533 0.06533 0.06198 -0.0809 1.0000 0.0086
-17.000 -0.8481 0.06272 0.05933 -0.0823 1.0000 0.0087
-16.750 -0.8440 0.06005 0.05661 -0.0837 1.0000 0.0088
-16.500 -0.8381 0.05765 0.05417 -0.0849 1.0000 0.0089
-16.250 -0.8336 0.05514 0.05162 -0.0861 1.0000 0.0090
-16.000 -0.8307 0.05259 0.04899 -0.0871 1.0000 0.0091
-15.750 -0.8226 0.05062 0.04700 -0.0881 1.0000 0.0093
-15.500 -0.8214 0.04779 0.04408 -0.0888 0.9723 0.0093
-15.250 -0.7792 0.04476 0.04092 -0.0978 0.9520 0.0098
-15.000 -0.7303 0.04120 0.03712 -0.1090 0.9367 0.0107
-14.750 -0.6853 0.03885 0.03454 -0.1177 0.8995 0.0109
-14.500 -0.6761 0.03753 0.03304 -0.1181 0.8640 0.0111
-14.250 -0.6710 0.03628 0.03160 -0.1175 0.8338 0.0114
-14.000 -0.6657 0.03492 0.03009 -0.1174 0.8174 0.0121
-13.750 -0.6649 0.03338 0.02831 -0.1171 0.7976 0.0127
-13.500 -0.6611 0.03202 0.02676 -0.1166 0.7786 0.0129
-13.250 -0.6583 0.03064 0.02523 -0.1161 0.7654 0.0133
-13.000 -0.6459 0.02979 0.02430 -0.1154 0.7446 0.0135
-12.750 -0.6329 0.02897 0.02348 -0.1149 0.7357 0.0140
-12.500 -0.6214 0.02801 0.02243 -0.1142 0.7219 0.0141
-12.000 -0.6083 0.02604 0.02021 -0.1129 0.7015 0.0152
-11.500 -0.6097 0.02435 0.01818 -0.1098 0.6825 0.0157
-11.250 -0.5648 0.02356 0.01754 -0.1104 0.6732 0.0167
-11.000 -0.5486 0.02286 0.01681 -0.1097 0.6642 0.0170
-10.750 -0.5347 0.02216 0.01602 -0.1087 0.6533 0.0175
-10.500 -0.5233 0.02147 0.01523 -0.1078 0.6457 0.0179
-10.250 -0.5213 0.02086 0.01447 -0.1059 0.6388 0.0183
-10.000 -0.5223 0.02048 0.01395 -0.1029 0.6314 0.0184
-9.750 -0.4791 0.01918 0.01282 -0.1043 0.6248 0.0192
-9.500 -0.4670 0.01847 0.01208 -0.1028 0.6194 0.0193
-9.250 -0.4620 0.01774 0.01134 -0.1004 0.6131 0.0198
-9.000 -0.4502 0.01715 0.01070 -0.0989 0.6074 0.0201
-8.750 -0.4331 0.01662 0.01013 -0.0980 0.6027 0.0204
-8.500 -0.4141 0.01618 0.00963 -0.0972 0.5971 0.0207
-8.250 -0.3947 0.01575 0.00913 -0.0965 0.5903 0.0207
-8.000 -0.3723 0.01542 0.00875 -0.0961 0.5840 0.0209
-7.750 -0.3518 0.01489 0.00818 -0.0956 0.5792 0.0211
-7.500 -0.3305 0.01440 0.00764 -0.0951 0.5739 0.0211
-7.250 -0.3090 0.01388 0.00707 -0.0947 0.5683 0.0213
-7.000 -0.2854 0.01343 0.00658 -0.0946 0.5642 0.0215
-6.750 -0.2609 0.01301 0.00613 -0.0946 0.5597 0.0217
-6.500 -0.2362 0.01260 0.00568 -0.0946 0.5543 0.0220
-6.250 -0.2107 0.01229 0.00531 -0.0946 0.5471 0.0223
-6.000 -0.1840 0.01197 0.00495 -0.0948 0.5414 0.0227
-5.750 -0.1570 0.01171 0.00464 -0.0950 0.5347 0.0231
-5.500 -0.1299 0.01150 0.00437 -0.0952 0.5279 0.0234
-5.250 -0.1019 0.01131 0.00414 -0.0955 0.5236 0.0236
-5.000 -0.0736 0.01113 0.00394 -0.0959 0.5176 0.0236
-4.750 -0.0456 0.01101 0.00376 -0.0961 0.5089 0.0237
-4.500 -0.0174 0.01090 0.00360 -0.0964 0.5002 0.0238
-4.250 0.0106 0.01083 0.00346 -0.0967 0.4907 0.0240
-4.000 0.0390 0.01075 0.00334 -0.0970 0.4835 0.0242
-3.750 0.0676 0.01067 0.00323 -0.0973 0.4772 0.0244
-3.500 0.0958 0.01063 0.00314 -0.0976 0.4690 0.0247
-3.250 0.1246 0.01056 0.00306 -0.0980 0.4636 0.0251
-3.000 0.1534 0.01050 0.00300 -0.0983 0.4547 0.0257
-2.750 0.1792 0.01067 0.00302 -0.0983 0.4170 0.0262
-2.500 0.1954 0.01163 0.00343 -0.0967 0.2921 0.0306
-2.250 0.2175 0.01211 0.00365 -0.0961 0.2238 0.0317
-2.000 0.2423 0.01239 0.00377 -0.0958 0.1763 0.0323
-1.750 0.2696 0.01247 0.00381 -0.0959 0.1655 0.0328
-1.500 0.2955 0.01265 0.00389 -0.0959 0.1311 0.0337
-1.250 0.3228 0.01272 0.00394 -0.0960 0.1242 0.0347
-1.000 0.3505 0.01277 0.00397 -0.0962 0.1197 0.0356
-0.750 0.3766 0.01293 0.00405 -0.0961 0.0932 0.0361
-0.500 0.4037 0.01301 0.00410 -0.0962 0.0885 0.0362
-0.250 0.4311 0.01306 0.00415 -0.0964 0.0859 0.0365
0.000 0.4584 0.01312 0.00420 -0.0965 0.0841 0.0370
0.250 0.4853 0.01321 0.00427 -0.0966 0.0810 0.0375
0.500 0.5122 0.01328 0.00434 -0.0967 0.0789 0.0384
0.750 0.5392 0.01335 0.00440 -0.0968 0.0767 0.0395
1.000 0.5647 0.01351 0.00451 -0.0966 0.0599 0.0406
1.250 0.5905 0.01363 0.00460 -0.0966 0.0577 0.0428
1.500 0.6164 0.01374 0.00471 -0.0965 0.0561 0.0450
1.750 0.6422 0.01384 0.00484 -0.0964 0.0551 0.0607
2.000 0.6677 0.01397 0.00498 -0.0962 0.0544 0.0650
2.250 0.6928 0.01410 0.00512 -0.0960 0.0537 0.0714
2.500 0.7177 0.01421 0.00528 -0.0958 0.0531 0.1001
2.750 0.7418 0.01437 0.00545 -0.0955 0.0524 0.1081
3.000 0.7657 0.01449 0.00563 -0.0951 0.0518 0.1421
3.250 0.7896 0.01456 0.00581 -0.0949 0.0514 0.1926
3.500 0.8131 0.01462 0.00599 -0.0946 0.0509 0.2505
3.750 0.8355 0.01462 0.00617 -0.0942 0.0504 0.3233
4.000 0.8575 0.01452 0.00637 -0.0938 0.0498 0.4305
4.250 0.8760 0.01471 0.00660 -0.0924 0.0496 0.4475
4.500 0.8951 0.01492 0.00691 -0.0913 0.0493 0.4737
4.750 0.9132 0.01519 0.00724 -0.0900 0.0490 0.4911
5.000 0.9308 0.01552 0.00759 -0.0887 0.0485 0.5007
5.250 0.9481 0.01587 0.00797 -0.0874 0.0481 0.5078
5.500 0.9649 0.01626 0.00839 -0.0861 0.0476 0.5138
5.750 0.9811 0.01670 0.00886 -0.0848 0.0471 0.5187
6.000 0.9973 0.01717 0.00938 -0.0836 0.0465 0.5292
6.250 1.0129 0.01769 0.00994 -0.0823 0.0460 0.5376
6.500 1.0280 0.01828 0.01056 -0.0811 0.0455 0.5439
6.750 1.0426 0.01892 0.01124 -0.0799 0.0449 0.5496
7.000 1.0578 0.01957 0.01192 -0.0788 0.0446 0.5567
7.250 1.0725 0.02028 0.01267 -0.0778 0.0442 0.5626
7.500 1.0870 0.02103 0.01347 -0.0768 0.0436 0.5692
7.750 1.1011 0.02183 0.01432 -0.0758 0.0423 0.5767
8.000 1.1135 0.02277 0.01529 -0.0747 0.0359 0.5852
8.250 1.1251 0.02381 0.01637 -0.0737 0.0357 0.5931
8.500 1.1364 0.02490 0.01749 -0.0726 0.0354 0.6000
8.750 1.1470 0.02607 0.01869 -0.0717 0.0349 0.6086
9.000 1.1573 0.02732 0.01997 -0.0707 0.0344 0.6177
9.250 1.1678 0.02857 0.02128 -0.0698 0.0341 0.6256
9.500 1.1774 0.02991 0.02267 -0.0689 0.0335 0.6362
9.750 1.1869 0.03131 0.02412 -0.0681 0.0331 0.6439
10.000 1.1970 0.03267 0.02556 -0.0674 0.0329 0.6538
10.250 1.2060 0.03416 0.02712 -0.0666 0.0326 0.6655
10.500 1.2155 0.03564 0.02866 -0.0660 0.0324 0.6784
10.750 1.2237 0.03727 0.03039 -0.0653 0.0322 0.6900
11.000 1.2325 0.03889 0.03207 -0.0648 0.0321 0.7019
11.250 1.2405 0.04061 0.03389 -0.0642 0.0319 0.7172
11.500 1.2488 0.04231 0.03570 -0.0637 0.0318 0.7373
11.750 1.2550 0.04427 0.03776 -0.0632 0.0315 0.7562
12.000 1.2613 0.04618 0.03981 -0.0627 0.0311 0.7843
12.250 1.2677 0.04809 0.04187 -0.0622 0.0310 0.8222
12.500 1.2690 0.04985 0.04400 -0.0608 0.0306 1.0000
12.750 1.2724 0.05231 0.04651 -0.0605 0.0302 1.0000
13.000 1.2780 0.05457 0.04881 -0.0603 0.0300 1.0000
13.250 1.2820 0.05703 0.05131 -0.0602 0.0296 1.0000
13.500 1.2853 0.05966 0.05399 -0.0601 0.0293 1.0000
13.750 1.2901 0.06214 0.05651 -0.0601 0.0291 1.0000
14.000 1.2939 0.06474 0.05918 -0.0601 0.0287 1.0000
14.250 1.3010 0.06707 0.06155 -0.0603 0.0285 1.0000
14.500 1.3091 0.06927 0.06380 -0.0605 0.0280 1.0000
14.750 1.3161 0.07161 0.06619 -0.0607 0.0277 1.0000
15.000 1.3207 0.07430 0.06892 -0.0610 0.0273 1.0000
15.250 1.3261 0.07692 0.07159 -0.0613 0.0270 1.0000
15.500 1.3316 0.07952 0.07424 -0.0616 0.0267 1.0000
15.750 1.3355 0.08237 0.07713 -0.0621 0.0263 1.0000
16.000 1.3376 0.08552 0.08031 -0.0626 0.0260 1.0000
16.250 1.3409 0.08845 0.08327 -0.0630 0.0257 1.0000
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