FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 200,000 Max Cl/Cd: 85.21 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100sm-il-200000.txt Download as CSV file: xf-fx60100sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX60-100 10.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3759 0.10095 0.09737 -0.0411 1.0000 0.0465
-9.250 -0.3789 0.09754 0.09402 -0.0432 1.0000 0.0467
-9.000 -0.3856 0.09235 0.08893 -0.0442 1.0000 0.0473
-8.750 -0.3720 0.09022 0.08678 -0.0403 1.0000 0.0488
-8.500 -0.3676 0.08809 0.08468 -0.0390 1.0000 0.0500
-8.250 -0.3682 0.08577 0.08241 -0.0383 1.0000 0.0513
-8.000 -0.3739 0.08345 0.08016 -0.0373 1.0000 0.0526
-7.750 -0.3856 0.08139 0.07818 -0.0356 1.0000 0.0537
-7.500 -0.4039 0.07973 0.07662 -0.0328 1.0000 0.0544
-7.250 -0.4237 0.07810 0.07508 -0.0300 1.0000 0.0548
-7.000 -0.4388 0.07516 0.07222 -0.0304 1.0000 0.0559
-6.500 -0.4414 0.05553 0.05223 -0.0597 0.9964 0.0605
-6.250 -0.4158 0.05411 0.05097 -0.0590 0.9937 0.0630
-6.000 -0.3765 0.04564 0.04184 -0.0746 0.9875 0.0737
-5.750 -0.3461 0.04320 0.03954 -0.0765 0.9844 0.0778
-5.500 -0.3098 0.03895 0.03498 -0.0832 0.9801 0.0900
-5.250 -0.2750 0.03587 0.03168 -0.0876 0.9753 0.1041
-5.000 -0.2368 0.03328 0.02894 -0.0918 0.9719 0.1208
-4.750 -0.1706 0.02313 0.01635 -0.0954 0.9715 0.0357
-4.500 -0.1294 0.02099 0.01393 -0.0981 0.9695 0.0357
-4.250 -0.0977 0.01918 0.01198 -0.0989 0.9640 0.0355
-4.000 -0.0603 0.01761 0.01035 -0.1007 0.9602 0.0361
-3.750 -0.0194 0.01606 0.00883 -0.1036 0.9574 0.0388
-3.500 0.0234 0.01530 0.00804 -0.1067 0.9546 0.0457
-3.250 0.0571 0.01449 0.00715 -0.1080 0.9477 0.0559
-3.000 0.1002 0.01260 0.00654 -0.1123 0.9448 0.3737
-2.750 0.1433 0.01258 0.00659 -0.1151 0.9417 0.4444
-2.500 0.1759 0.01269 0.00675 -0.1157 0.9346 0.4864
-2.250 0.2144 0.01265 0.00669 -0.1174 0.9298 0.5129
-2.000 0.2554 0.01247 0.00647 -0.1197 0.9265 0.5303
-1.750 0.2848 0.01239 0.00637 -0.1197 0.9178 0.5453
-1.500 0.3222 0.01219 0.00614 -0.1212 0.9130 0.5611
-1.250 0.3519 0.01207 0.00603 -0.1212 0.9046 0.5750
-1.000 0.3860 0.01186 0.00582 -0.1219 0.8985 0.5892
-0.750 0.4143 0.01174 0.00570 -0.1217 0.8892 0.6024
-0.500 0.4467 0.01152 0.00548 -0.1220 0.8827 0.6164
-0.250 0.4735 0.01141 0.00540 -0.1214 0.8719 0.6301
0.000 0.5017 0.01127 0.00528 -0.1210 0.8623 0.6445
0.250 0.5310 0.01109 0.00510 -0.1207 0.8536 0.6596
0.500 0.5574 0.01098 0.00504 -0.1200 0.8417 0.6752
0.750 0.5842 0.01086 0.00496 -0.1193 0.8298 0.6920
1.000 0.6111 0.01074 0.00488 -0.1186 0.8176 0.7103
1.250 0.6376 0.01061 0.00480 -0.1179 0.8050 0.7295
1.500 0.6637 0.01049 0.00474 -0.1170 0.7916 0.7512
1.750 0.6892 0.01037 0.00469 -0.1161 0.7774 0.7762
2.000 0.7134 0.01024 0.00464 -0.1148 0.7622 0.8076
2.250 0.7353 0.01005 0.00456 -0.1130 0.7459 0.8553
2.500 0.7605 0.00982 0.00442 -0.1119 0.7283 1.0000
2.750 0.7897 0.00992 0.00440 -0.1120 0.7097 1.0000
3.000 0.8172 0.01004 0.00443 -0.1117 0.6876 1.0000
3.250 0.8441 0.01019 0.00445 -0.1113 0.6642 1.0000
3.500 0.8704 0.01037 0.00456 -0.1108 0.6388 1.0000
3.750 0.8964 0.01058 0.00468 -0.1103 0.6138 1.0000
4.000 0.9222 0.01084 0.00483 -0.1097 0.5884 1.0000
4.250 0.9475 0.01112 0.00501 -0.1091 0.5623 1.0000
4.500 0.9726 0.01143 0.00525 -0.1085 0.5350 1.0000
4.750 0.9973 0.01176 0.00550 -0.1078 0.5073 1.0000
5.000 1.0215 0.01214 0.00578 -0.1071 0.4774 1.0000
5.250 1.0450 0.01255 0.00609 -0.1063 0.4451 1.0000
5.500 1.0683 0.01300 0.00646 -0.1055 0.4110 1.0000
5.750 1.0905 0.01354 0.00685 -0.1045 0.3742 1.0000
6.000 1.1117 0.01417 0.00731 -0.1035 0.3307 1.0000
6.250 1.1317 0.01494 0.00786 -0.1023 0.2806 1.0000
6.500 1.1499 0.01592 0.00856 -0.1010 0.2301 1.0000
6.750 1.1680 0.01698 0.00936 -0.0997 0.1891 1.0000
7.000 1.1865 0.01801 0.01022 -0.0984 0.1621 1.0000
7.250 1.2052 0.01903 0.01112 -0.0971 0.1445 1.0000
7.500 1.2238 0.02005 0.01206 -0.0958 0.1319 1.0000
7.750 1.2443 0.02087 0.01295 -0.0948 0.1219 1.0000
8.000 1.2636 0.02184 0.01395 -0.0936 0.1134 1.0000
8.250 1.2818 0.02297 0.01501 -0.0923 0.1060 1.0000
8.500 1.3020 0.02379 0.01597 -0.0912 0.0992 1.0000
8.750 1.3196 0.02506 0.01716 -0.0900 0.0924 1.0000
9.000 1.3390 0.02576 0.01808 -0.0887 0.0862 1.0000
9.250 1.3556 0.02699 0.01925 -0.0875 0.0798 1.0000
9.500 1.3727 0.02774 0.02021 -0.0860 0.0739 1.0000
9.750 1.3868 0.02884 0.02129 -0.0844 0.0679 1.0000
10.000 1.3998 0.02976 0.02241 -0.0824 0.0621 1.0000
10.250 1.4091 0.03077 0.02343 -0.0801 0.0565 1.0000
10.500 1.4185 0.03192 0.02477 -0.0779 0.0505 1.0000
10.750 1.4242 0.03323 0.02607 -0.0755 0.0452 1.0000
11.000 1.4316 0.03460 0.02767 -0.0733 0.0398 1.0000
11.250 1.4352 0.03626 0.02934 -0.0712 0.0357 1.0000
11.500 1.4397 0.03839 0.03167 -0.0690 0.0320 1.0000
11.750 1.4442 0.04012 0.03350 -0.0673 0.0291 1.0000
12.000 1.4430 0.04298 0.03637 -0.0655 0.0267 1.0000
12.250 1.4460 0.04526 0.03891 -0.0640 0.0249 1.0000
12.500 1.4476 0.04781 0.04165 -0.0628 0.0233 1.0000
12.750 1.4480 0.05054 0.04452 -0.0617 0.0221 1.0000
13.000 1.4471 0.05351 0.04760 -0.0610 0.0212 1.0000
13.250 1.4434 0.05721 0.05143 -0.0603 0.0204 1.0000
13.500 1.4348 0.06223 0.05667 -0.0597 0.0198 1.0000
13.750 1.4276 0.06642 0.06113 -0.0599 0.0195 1.0000
14.000 1.4182 0.07115 0.06612 -0.0605 0.0192 1.0000
14.250 1.4064 0.07644 0.07168 -0.0617 0.0190 1.0000
14.500 1.3926 0.08228 0.07777 -0.0636 0.0189 1.0000
14.750 1.3769 0.08876 0.08452 -0.0662 0.0188 1.0000
15.000 1.3595 0.09593 0.09192 -0.0696 0.0188 1.0000
15.250 1.3405 0.10381 0.10005 -0.0738 0.0188 1.0000
15.500 1.3205 0.11244 0.10889 -0.0789 0.0189 1.0000
15.750 1.2994 0.12185 0.11852 -0.0849 0.0190 1.0000
16.000 1.2769 0.13216 0.12902 -0.0917 0.0192 1.0000
16.250 1.2536 0.14337 0.14040 -0.0994 0.0195 1.0000
16.500 1.2272 0.15618 0.15334 -0.1081 0.0198 1.0000
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Polar data table (+)
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