FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 100,000 Max Cl/Cd: 61.57 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100sm-il-100000-n5.txt Download as CSV file: xf-fx60100sm-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3807 0.08919 0.08418 -0.0425 1.0000 0.0261
-8.750 -0.3811 0.08618 0.08124 -0.0424 1.0000 0.0257
-8.500 -0.3838 0.08304 0.07817 -0.0425 1.0000 0.0253
-8.250 -0.3893 0.07992 0.07511 -0.0424 1.0000 0.0250
-8.000 -0.3995 0.07679 0.07209 -0.0419 1.0000 0.0246
-7.750 -0.4145 0.07391 0.06935 -0.0407 1.0000 0.0243
-7.500 -0.4287 0.07016 0.06570 -0.0409 1.0000 0.0240
-7.250 -0.4410 0.06486 0.06045 -0.0439 1.0000 0.0235
-7.000 -0.4510 0.05778 0.05330 -0.0512 1.0000 0.0230
-6.750 -0.4447 0.05040 0.04559 -0.0599 0.9979 0.0224
-6.500 -0.4131 0.04324 0.03783 -0.0703 0.9922 0.0226
-6.250 -0.3790 0.03826 0.03223 -0.0770 0.9872 0.0239
-6.000 -0.3418 0.03417 0.02744 -0.0823 0.9835 0.0248
-5.750 -0.3076 0.03092 0.02364 -0.0855 0.9791 0.0249
-5.500 -0.2726 0.02827 0.02051 -0.0881 0.9749 0.0251
-5.250 -0.2361 0.02611 0.01793 -0.0904 0.9715 0.0256
-5.000 -0.2007 0.02443 0.01593 -0.0922 0.9678 0.0261
-4.750 -0.1693 0.02279 0.01414 -0.0932 0.9627 0.0270
-4.500 -0.1347 0.02147 0.01283 -0.0951 0.9586 0.0298
-4.250 -0.0970 0.02051 0.01177 -0.0974 0.9553 0.0333
-4.000 -0.0658 0.01969 0.01081 -0.0982 0.9488 0.0355
-3.750 -0.0285 0.01866 0.00967 -0.1005 0.9443 0.0403
-3.500 0.0120 0.01782 0.00874 -0.1033 0.9409 0.0522
-3.250 0.0457 0.01647 0.00786 -0.1054 0.9346 0.1446
-3.000 0.0824 0.01556 0.00782 -0.1079 0.9298 0.3714
-2.750 0.1185 0.01564 0.00805 -0.1093 0.9251 0.4552
-2.500 0.1483 0.01561 0.00792 -0.1095 0.9169 0.4787
-2.250 0.1847 0.01551 0.00771 -0.1108 0.9120 0.4978
-2.000 0.2136 0.01546 0.00759 -0.1109 0.9033 0.5146
-1.750 0.2491 0.01533 0.00739 -0.1120 0.8978 0.5313
-1.500 0.2778 0.01527 0.00727 -0.1120 0.8887 0.5458
-1.250 0.3125 0.01512 0.00707 -0.1130 0.8827 0.5604
-1.000 0.3404 0.01506 0.00699 -0.1127 0.8728 0.5739
-0.750 0.3721 0.01493 0.00684 -0.1131 0.8651 0.5879
-0.500 0.4018 0.01483 0.00673 -0.1132 0.8559 0.6019
-0.250 0.4304 0.01475 0.00666 -0.1130 0.8459 0.6160
0.000 0.4615 0.01462 0.00652 -0.1132 0.8373 0.6308
0.250 0.4898 0.01454 0.00646 -0.1129 0.8265 0.6460
0.500 0.5177 0.01447 0.00641 -0.1126 0.8151 0.6619
0.750 0.5461 0.01439 0.00636 -0.1123 0.8038 0.6790
1.000 0.5747 0.01430 0.00630 -0.1120 0.7924 0.6975
1.250 0.6025 0.01418 0.00623 -0.1115 0.7805 0.7169
1.500 0.6292 0.01410 0.00621 -0.1108 0.7669 0.7393
1.750 0.6550 0.01400 0.00621 -0.1099 0.7528 0.7649
2.000 0.6798 0.01388 0.00618 -0.1088 0.7380 0.7975
2.500 0.7288 0.01355 0.00605 -0.1063 0.7056 1.0000
2.750 0.7576 0.01368 0.00615 -0.1063 0.6877 1.0000
3.000 0.7859 0.01382 0.00622 -0.1062 0.6689 1.0000
3.250 0.8138 0.01398 0.00630 -0.1060 0.6491 1.0000
3.500 0.8406 0.01417 0.00644 -0.1056 0.6267 1.0000
3.750 0.8671 0.01439 0.00661 -0.1051 0.6024 1.0000
4.000 0.8929 0.01465 0.00677 -0.1044 0.5750 1.0000
4.250 0.9179 0.01496 0.00697 -0.1037 0.5454 1.0000
4.500 0.9425 0.01531 0.00722 -0.1029 0.5151 1.0000
4.750 0.9667 0.01570 0.00754 -0.1022 0.4844 1.0000
5.000 0.9905 0.01614 0.00789 -0.1014 0.4530 1.0000
5.250 1.0136 0.01663 0.00827 -0.1005 0.4202 1.0000
5.500 1.0361 0.01717 0.00873 -0.0996 0.3862 1.0000
5.750 1.0581 0.01776 0.00922 -0.0987 0.3503 1.0000
6.000 1.0792 0.01844 0.00976 -0.0977 0.3138 1.0000
6.250 1.0995 0.01921 0.01038 -0.0966 0.2753 1.0000
6.500 1.1192 0.02006 0.01108 -0.0955 0.2379 1.0000
6.750 1.1385 0.02098 0.01189 -0.0944 0.2059 1.0000
7.000 1.1575 0.02192 0.01274 -0.0933 0.1798 1.0000
7.250 1.1758 0.02294 0.01366 -0.0921 0.1593 1.0000
7.500 1.1943 0.02391 0.01461 -0.0909 0.1432 1.0000
7.750 1.2120 0.02495 0.01563 -0.0896 0.1315 1.0000
8.000 1.2302 0.02594 0.01672 -0.0883 0.1214 1.0000
8.250 1.2476 0.02698 0.01782 -0.0870 0.1128 1.0000
8.500 1.2631 0.02814 0.01897 -0.0855 0.1056 1.0000
8.750 1.2807 0.02920 0.02018 -0.0842 0.0991 1.0000
9.000 1.2955 0.03040 0.02142 -0.0826 0.0932 1.0000
9.250 1.3117 0.03156 0.02273 -0.0812 0.0871 1.0000
9.500 1.3256 0.03276 0.02405 -0.0796 0.0816 1.0000
9.750 1.3381 0.03407 0.02547 -0.0778 0.0764 1.0000
10.000 1.3496 0.03526 0.02682 -0.0760 0.0707 1.0000
10.250 1.3580 0.03673 0.02832 -0.0740 0.0661 1.0000
10.500 1.3685 0.03805 0.02991 -0.0721 0.0605 1.0000
10.750 1.3742 0.03956 0.03149 -0.0702 0.0562 1.0000
11.000 1.3815 0.04126 0.03342 -0.0684 0.0513 1.0000
11.250 1.3864 0.04299 0.03531 -0.0667 0.0470 1.0000
11.500 1.3880 0.04512 0.03754 -0.0651 0.0436 1.0000
11.750 1.3922 0.04734 0.04005 -0.0637 0.0395 1.0000
12.000 1.3927 0.04967 0.04251 -0.0625 0.0365 1.0000
12.250 1.3903 0.05252 0.04545 -0.0615 0.0341 1.0000
12.500 1.3900 0.05555 0.04878 -0.0607 0.0314 1.0000
12.750 1.3869 0.05884 0.05226 -0.0602 0.0294 1.0000
13.000 1.3822 0.06237 0.05594 -0.0602 0.0279 1.0000
13.250 1.3748 0.06640 0.06008 -0.0607 0.0268 1.0000
13.500 1.3670 0.07095 0.06486 -0.0613 0.0256 1.0000
13.750 1.3579 0.07590 0.07011 -0.0625 0.0245 1.0000
14.000 1.3472 0.08131 0.07577 -0.0643 0.0236 1.0000
14.250 1.3348 0.08720 0.08189 -0.0666 0.0229 1.0000
14.500 1.3214 0.09362 0.08852 -0.0696 0.0224 1.0000
14.750 1.3067 0.10067 0.09578 -0.0732 0.0220 1.0000
15.000 1.2902 0.10847 0.10379 -0.0776 0.0218 1.0000
15.250 1.2711 0.11736 0.11291 -0.0828 0.0218 1.0000
15.500 1.2469 0.12820 0.12400 -0.0896 0.0221 1.0000
15.750 1.2085 0.14393 0.13999 -0.0996 0.0234 1.0000
16.000 1.1697 0.16157 0.15776 -0.1108 0.0250 1.0000
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Polar data table (+)
Polar graphs
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