FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX S 02-196 AIRFOIL (fxs02196-il) Reynolds number: 500,000 Max Cl/Cd: 46.54 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxs02196-il-500000-n5.txt Download as CSV file: xf-fxs02196-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5879 0.10783 0.10507 -0.0609 1.0000 0.0091
-17.000 -0.6557 0.09017 0.08706 -0.0710 1.0000 0.0089
-16.750 -0.6769 0.08256 0.07929 -0.0754 1.0000 0.0090
-16.500 -0.6909 0.07657 0.07317 -0.0788 1.0000 0.0091
-16.250 -0.6958 0.07075 0.06719 -0.0832 0.9670 0.0093
-16.000 -0.6835 0.06405 0.06024 -0.0931 0.9433 0.0096
-15.750 -0.6659 0.05715 0.05290 -0.1043 0.9207 0.0106
-15.500 -0.6459 0.05326 0.04875 -0.1110 0.8886 0.0107
-15.000 -0.6377 0.04863 0.04368 -0.1133 0.8356 0.0113
-14.750 -0.6364 0.04641 0.04127 -0.1136 0.8174 0.0116
-14.500 -0.6350 0.04429 0.03894 -0.1139 0.8013 0.0121
-14.250 -0.6336 0.04229 0.03671 -0.1141 0.7872 0.0125
-14.000 -0.6342 0.04029 0.03444 -0.1142 0.7741 0.0129
-13.750 -0.6315 0.03855 0.03251 -0.1143 0.7617 0.0132
-13.500 -0.6226 0.03726 0.03113 -0.1139 0.7499 0.0133
-13.250 -0.6133 0.03604 0.02985 -0.1136 0.7386 0.0135
-13.000 -0.6043 0.03481 0.02852 -0.1133 0.7288 0.0137
-12.750 -0.5950 0.03364 0.02726 -0.1129 0.7189 0.0141
-12.500 -0.5849 0.03250 0.02601 -0.1124 0.7101 0.0142
-12.250 -0.5752 0.03138 0.02478 -0.1120 0.7011 0.0146
-12.000 -0.5656 0.03030 0.02357 -0.1115 0.6919 0.0150
-11.750 -0.5539 0.02932 0.02248 -0.1109 0.6838 0.0151
-11.500 -0.5451 0.02831 0.02130 -0.1103 0.6756 0.0154
-11.250 -0.5385 0.02734 0.02015 -0.1097 0.6680 0.0157
-11.000 -0.5281 0.02649 0.01917 -0.1090 0.6608 0.0158
-10.750 -0.5026 0.02580 0.01858 -0.1082 0.6531 0.0163
-10.500 -0.4872 0.02504 0.01779 -0.1073 0.6455 0.0166
-10.250 -0.4726 0.02428 0.01700 -0.1065 0.6376 0.0170
-9.750 -0.4441 0.02285 0.01544 -0.1046 0.6223 0.0173
-9.500 -0.4303 0.02213 0.01467 -0.1036 0.6156 0.0174
-9.250 -0.4172 0.02148 0.01392 -0.1025 0.6070 0.0178
-9.000 -0.4040 0.02080 0.01319 -0.1014 0.6007 0.0179
-8.750 -0.3919 0.02022 0.01252 -0.1000 0.5953 0.0182
-8.500 -0.3833 0.01968 0.01190 -0.0981 0.5895 0.0185
-8.250 -0.3698 0.01901 0.01121 -0.0970 0.5856 0.0186
-8.000 -0.3575 0.01817 0.01039 -0.0957 0.5802 0.0190
-7.750 -0.3409 0.01754 0.00974 -0.0948 0.5757 0.0192
-7.500 -0.3216 0.01703 0.00918 -0.0942 0.5714 0.0194
-7.000 -0.2800 0.01604 0.00811 -0.0934 0.5644 0.0202
-6.750 -0.2570 0.01561 0.00765 -0.0932 0.5599 0.0206
-6.500 -0.2331 0.01526 0.00724 -0.0931 0.5545 0.0208
-6.250 -0.2088 0.01494 0.00686 -0.0929 0.5490 0.0208
-6.000 -0.1836 0.01464 0.00650 -0.0930 0.5447 0.0209
-5.750 -0.1576 0.01435 0.00618 -0.0931 0.5409 0.0209
-5.500 -0.1314 0.01407 0.00587 -0.0932 0.5375 0.0210
-5.250 -0.1048 0.01381 0.00558 -0.0934 0.5339 0.0211
-5.000 -0.0784 0.01361 0.00530 -0.0935 0.5279 0.0212
-4.750 -0.0512 0.01340 0.00506 -0.0937 0.5214 0.0213
-4.500 -0.0240 0.01322 0.00482 -0.0939 0.5124 0.0214
-4.250 0.0030 0.01308 0.00462 -0.0941 0.5046 0.0216
-4.000 0.0308 0.01293 0.00443 -0.0944 0.4982 0.0217
-3.750 0.0585 0.01281 0.00426 -0.0946 0.4920 0.0218
-3.500 0.0860 0.01272 0.00411 -0.0948 0.4851 0.0220
-3.250 0.1140 0.01262 0.00397 -0.0951 0.4784 0.0222
-3.000 0.1416 0.01255 0.00385 -0.0953 0.4700 0.0225
-2.750 0.1695 0.01248 0.00374 -0.0956 0.4626 0.0231
-2.500 0.1975 0.01242 0.00365 -0.0959 0.4514 0.0236
-2.250 0.2248 0.01242 0.00360 -0.0961 0.4344 0.0249
-2.000 0.2395 0.01333 0.00395 -0.0944 0.3077 0.0257
-1.750 0.2597 0.01391 0.00425 -0.0935 0.2382 0.0309
-1.500 0.2847 0.01411 0.00435 -0.0933 0.2196 0.0326
-1.250 0.3080 0.01442 0.00451 -0.0928 0.1729 0.0333
-1.000 0.3337 0.01456 0.00459 -0.0928 0.1426 0.0338
-0.750 0.3579 0.01478 0.00471 -0.0925 0.1255 0.0345
-0.500 0.3843 0.01487 0.00477 -0.0925 0.1215 0.0352
-0.250 0.4111 0.01492 0.00482 -0.0925 0.1188 0.0360
0.000 0.4362 0.01507 0.00492 -0.0924 0.0942 0.0367
0.250 0.4613 0.01521 0.00502 -0.0922 0.0888 0.0376
0.500 0.4870 0.01531 0.00510 -0.0921 0.0853 0.0389
0.750 0.5125 0.01542 0.00520 -0.0920 0.0825 0.0404
1.000 0.5375 0.01554 0.00532 -0.0917 0.0798 0.0414
1.250 0.5628 0.01564 0.00541 -0.0916 0.0774 0.0436
1.500 0.5868 0.01579 0.00557 -0.0913 0.0606 0.0626
1.750 0.6103 0.01596 0.00573 -0.0908 0.0591 0.0667
2.000 0.6334 0.01614 0.00589 -0.0903 0.0571 0.0711
2.250 0.6565 0.01627 0.00607 -0.0899 0.0558 0.1007
2.500 0.6791 0.01642 0.00625 -0.0893 0.0550 0.1115
2.750 0.7006 0.01653 0.00644 -0.0886 0.0543 0.1522
3.000 0.7202 0.01665 0.00663 -0.0876 0.0536 0.1929
3.250 0.7389 0.01680 0.00686 -0.0864 0.0531 0.2142
3.500 0.7594 0.01681 0.00710 -0.0859 0.0524 0.3150
3.750 0.7808 0.01680 0.00745 -0.0857 0.0519 0.4421
4.000 0.7981 0.01715 0.00787 -0.0844 0.0513 0.4585
4.250 0.8151 0.01754 0.00833 -0.0832 0.0510 0.4751
4.500 0.8312 0.01799 0.00884 -0.0819 0.0505 0.4901
4.750 0.8470 0.01849 0.00936 -0.0806 0.0502 0.4987
5.000 0.8630 0.01900 0.00992 -0.0794 0.0499 0.5076
5.250 0.8790 0.01954 0.01052 -0.0783 0.0497 0.5185
5.500 0.8950 0.02011 0.01116 -0.0773 0.0491 0.5269
5.750 0.9103 0.02075 0.01185 -0.0762 0.0485 0.5345
6.000 0.9253 0.02145 0.01259 -0.0752 0.0476 0.5405
6.250 0.9401 0.02219 0.01339 -0.0742 0.0467 0.5494
6.500 0.9543 0.02300 0.01424 -0.0733 0.0459 0.5573
6.750 0.9682 0.02385 0.01514 -0.0724 0.0448 0.5623
7.000 0.9825 0.02472 0.01606 -0.0715 0.0440 0.5678
7.250 0.9966 0.02562 0.01702 -0.0707 0.0428 0.5717
7.500 1.0099 0.02661 0.01805 -0.0699 0.0357 0.5771
7.750 1.0193 0.02791 0.01937 -0.0689 0.0351 0.5811
8.000 1.0296 0.02917 0.02066 -0.0680 0.0344 0.5873
8.250 1.0406 0.03042 0.02196 -0.0672 0.0338 0.5929
8.500 1.0513 0.03173 0.02330 -0.0665 0.0333 0.5986
8.750 1.0622 0.03302 0.02465 -0.0658 0.0329 0.6053
9.000 1.0726 0.03441 0.02609 -0.0651 0.0325 0.6122
9.250 1.0832 0.03579 0.02751 -0.0645 0.0323 0.6183
9.500 1.0932 0.03725 0.02904 -0.0639 0.0322 0.6240
9.750 1.1034 0.03872 0.03058 -0.0633 0.0320 0.6323
10.000 1.1133 0.04027 0.03220 -0.0629 0.0319 0.6412
10.250 1.1233 0.04182 0.03383 -0.0624 0.0317 0.6504
10.750 1.1427 0.04508 0.03726 -0.0616 0.0315 0.6732
11.000 1.1528 0.04670 0.03896 -0.0613 0.0313 0.6837
11.250 1.1618 0.04846 0.04082 -0.0610 0.0312 0.6964
11.500 1.1712 0.05021 0.04266 -0.0607 0.0310 0.7088
12.000 1.1874 0.05405 0.04670 -0.0603 0.0305 0.7386
12.250 1.1949 0.05606 0.04883 -0.0601 0.0302 0.7564
12.500 1.2017 0.05814 0.05102 -0.0599 0.0298 0.7792
12.750 1.2058 0.06047 0.05350 -0.0595 0.0294 0.8105
13.000 1.2085 0.06233 0.05563 -0.0583 0.0291 0.8895
13.250 1.2142 0.06453 0.05794 -0.0584 0.0289 1.0000
13.500 1.2212 0.06686 0.06031 -0.0585 0.0287 1.0000
13.750 1.2293 0.06908 0.06258 -0.0587 0.0285 1.0000
14.000 1.2373 0.07132 0.06487 -0.0589 0.0284 1.0000
14.250 1.2446 0.07368 0.06729 -0.0592 0.0282 1.0000
14.500 1.2513 0.07615 0.06981 -0.0595 0.0279 1.0000
14.750 1.2582 0.07860 0.07231 -0.0598 0.0275 1.0000
15.000 1.2643 0.08117 0.07494 -0.0602 0.0270 1.0000
15.250 1.2687 0.08402 0.07784 -0.0606 0.0267 1.0000
15.500 1.2740 0.08676 0.08062 -0.0611 0.0264 1.0000
15.750 1.2785 0.08960 0.08351 -0.0617 0.0261 1.0000
16.000 1.2825 0.09253 0.08648 -0.0622 0.0258 1.0000
16.250 1.2856 0.09564 0.08962 -0.0629 0.0255 1.0000
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Polar data table (+)
Polar graphs
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