FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 50,000 Max Cl/Cd: 40.63 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100sm-il-50000.txt Download as CSV file: xf-fx60100sm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3691 0.12111 0.11401 -0.0256 1.0000 0.2144
-9.500 -0.3512 0.11651 0.10940 -0.0246 1.0000 0.2231
-9.250 -0.3620 0.11545 0.10847 -0.0256 1.0000 0.2288
-9.000 -0.3438 0.11092 0.10394 -0.0246 1.0000 0.2375
-8.750 -0.3506 0.10914 0.10227 -0.0250 1.0000 0.2440
-8.500 -0.3401 0.10581 0.09897 -0.0241 1.0000 0.2534
-8.250 -0.3398 0.10315 0.09638 -0.0237 1.0000 0.2600
-8.000 -0.3477 0.10207 0.09542 -0.0231 1.0000 0.2703
-7.750 -0.3316 0.09784 0.09121 -0.0218 1.0000 0.2799
-7.500 -0.3367 0.09584 0.08934 -0.0208 1.0000 0.2888
-7.250 -0.3447 0.09467 0.08830 -0.0193 1.0000 0.2990
-7.000 -0.3326 0.09093 0.08459 -0.0178 1.0000 0.3078
-6.750 -0.3577 0.09091 0.08479 -0.0151 1.0000 0.3157
-6.500 -0.3424 0.08707 0.08096 -0.0136 1.0000 0.3238
-5.500 -0.3928 0.05400 0.04755 -0.0587 1.0000 0.1258
-5.250 -0.3675 0.04684 0.03987 -0.0654 1.0000 0.1160
-5.000 -0.3358 0.04152 0.03381 -0.0706 1.0000 0.1111
-4.750 -0.3061 0.03753 0.02929 -0.0733 1.0000 0.1092
-4.500 -0.2746 0.03405 0.02526 -0.0754 1.0000 0.1072
-4.250 -0.2437 0.03134 0.02202 -0.0765 1.0000 0.1070
-4.000 -0.2144 0.02927 0.01952 -0.0769 1.0000 0.1096
-3.750 -0.1873 0.02758 0.01764 -0.0769 1.0000 0.1170
-3.500 -0.1609 0.02627 0.01613 -0.0764 1.0000 0.1267
-3.250 -0.1362 0.02492 0.01481 -0.0756 1.0000 0.1399
-3.000 -0.1062 0.02338 0.01356 -0.0764 1.0000 0.1805
-2.750 -0.0833 0.02285 0.01487 -0.0739 1.0000 0.5006
-2.500 -0.0809 0.02410 0.01634 -0.0670 1.0000 0.5702
-2.250 -0.0851 0.02508 0.01757 -0.0584 1.0000 0.6298
-2.000 -0.0751 0.02516 0.01756 -0.0543 1.0000 0.6697
-1.750 -0.0584 0.02494 0.01719 -0.0524 1.0000 0.6986
-1.500 -0.0403 0.02472 0.01681 -0.0510 1.0000 0.7267
-1.250 -0.0235 0.02450 0.01647 -0.0495 1.0000 0.7530
-1.000 -0.0062 0.02429 0.01615 -0.0482 1.0000 0.7799
-0.750 0.0112 0.02410 0.01585 -0.0471 1.0000 0.8079
-0.500 0.0279 0.02392 0.01561 -0.0460 1.0000 0.8383
-0.250 0.0431 0.02370 0.01538 -0.0447 1.0000 0.8738
0.000 0.0603 0.02336 0.01513 -0.0443 1.0000 0.9321
0.250 0.0919 0.02359 0.01522 -0.0489 1.0000 1.0000
0.500 0.1330 0.02441 0.01575 -0.0550 1.0000 1.0000
0.750 0.1685 0.02532 0.01640 -0.0596 1.0000 1.0000
1.000 0.2285 0.02679 0.01759 -0.0684 0.9853 1.0000
1.250 0.2862 0.02821 0.01878 -0.0760 0.9698 1.0000
1.500 0.3354 0.02939 0.01979 -0.0817 0.9532 1.0000
1.750 0.3798 0.03045 0.02074 -0.0862 0.9360 1.0000
2.000 0.4234 0.03146 0.02167 -0.0903 0.9187 1.0000
2.250 0.4669 0.03240 0.02257 -0.0940 0.9014 1.0000
2.500 0.5115 0.03324 0.02340 -0.0976 0.8844 1.0000
2.750 0.5565 0.03397 0.02415 -0.1010 0.8674 1.0000
3.000 0.5878 0.03472 0.02495 -0.1023 0.8480 1.0000
3.250 0.6273 0.03529 0.02558 -0.1044 0.8295 1.0000
3.500 0.6721 0.03563 0.02601 -0.1068 0.8119 1.0000
3.750 0.7137 0.03586 0.02638 -0.1085 0.7936 1.0000
4.000 0.7468 0.03621 0.02685 -0.1090 0.7731 1.0000
4.250 0.7975 0.03569 0.02651 -0.1109 0.7547 1.0000
4.500 0.8481 0.03470 0.02576 -0.1119 0.7363 1.0000
4.750 0.8826 0.03426 0.02548 -0.1110 0.7134 1.0000
5.000 0.9339 0.03240 0.02386 -0.1107 0.6920 1.0000
5.250 0.9776 0.03069 0.02231 -0.1093 0.6661 1.0000
5.500 1.0161 0.02923 0.02096 -0.1074 0.6367 1.0000
5.750 1.0464 0.02843 0.02025 -0.1050 0.6026 1.0000
6.000 1.0774 0.02762 0.01941 -0.1026 0.5645 1.0000
6.250 1.1027 0.02736 0.01905 -0.0999 0.5205 1.0000
6.500 1.1231 0.02764 0.01917 -0.0970 0.4697 1.0000
6.750 1.1426 0.02829 0.01950 -0.0942 0.4154 1.0000
7.000 1.1600 0.02954 0.02045 -0.0917 0.3637 1.0000
7.250 1.1787 0.03106 0.02170 -0.0897 0.3211 1.0000
7.500 1.2003 0.03273 0.02311 -0.0883 0.2884 1.0000
7.750 1.2221 0.03470 0.02509 -0.0872 0.2633 1.0000
8.000 1.2453 0.03662 0.02693 -0.0863 0.2424 1.0000
8.250 1.2670 0.03889 0.02937 -0.0853 0.2261 1.0000
8.500 1.2885 0.04129 0.03192 -0.0844 0.2121 1.0000
8.750 1.3078 0.04368 0.03446 -0.0833 0.1986 1.0000
9.000 1.3316 0.04649 0.03731 -0.0827 0.1876 1.0000
9.250 1.3396 0.04953 0.04095 -0.0804 0.1782 1.0000
9.500 1.3506 0.05282 0.04456 -0.0787 0.1691 1.0000
9.750 1.3706 0.05607 0.04784 -0.0779 0.1593 1.0000
10.000 1.3604 0.06021 0.05274 -0.0745 0.1545 1.0000
10.250 1.3774 0.06368 0.05619 -0.0736 0.1451 1.0000
10.500 1.3594 0.06847 0.06160 -0.0704 0.1432 1.0000
10.750 1.3381 0.07342 0.06698 -0.0676 0.1419 1.0000
11.000 1.3117 0.07847 0.07234 -0.0651 0.1420 1.0000
11.250 1.2822 0.08376 0.07783 -0.0633 0.1430 1.0000
11.500 1.2532 0.08986 0.08408 -0.0631 0.1442 1.0000
11.750 1.2264 0.09682 0.09115 -0.0644 0.1453 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX60-100 10.0% smoothed (fx60100sm-il)