FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 100,000 Max Cl/Cd: 62.76 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100sm-il-100000.txt Download as CSV file: xf-fx60100sm-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3542 0.10230 0.09733 -0.0336 1.0000 0.1070
-8.750 -0.3677 0.10041 0.09556 -0.0362 1.0000 0.1121
-8.500 -0.3997 0.09958 0.09494 -0.0395 1.0000 0.1132
-8.250 -0.3572 0.09400 0.08925 -0.0342 1.0000 0.1180
-8.000 -0.3598 0.09186 0.08719 -0.0338 1.0000 0.1237
-7.750 -0.3908 0.09099 0.08652 -0.0342 1.0000 0.1265
-7.500 -0.4302 0.08968 0.08541 -0.0378 1.0000 0.1274
-7.250 -0.3795 0.08562 0.08124 -0.0290 1.0000 0.1359
-7.000 -0.4050 0.08448 0.08025 -0.0275 1.0000 0.1395
-6.750 -0.4387 0.08084 0.07677 -0.0364 1.0000 0.1420
-6.500 -0.3940 0.07245 0.06880 -0.0230 1.0000 0.1554
-6.250 -0.3767 0.06918 0.06552 -0.0171 1.0000 0.1599
-6.000 -0.4263 0.07487 0.07093 -0.0238 1.0000 0.1607
-5.750 -0.4321 0.07051 0.06661 -0.0311 1.0000 0.1718
-5.500 -0.4260 0.06937 0.06551 -0.0249 1.0000 0.1764
-5.250 -0.4222 0.06561 0.06176 -0.0286 1.0000 0.1883
-5.000 -0.3289 0.03487 0.02833 -0.0726 1.0000 0.0707
-4.750 -0.2963 0.03044 0.02341 -0.0750 1.0000 0.0639
-4.500 -0.2630 0.02871 0.02078 -0.0757 1.0000 0.0590
-4.250 -0.2338 0.02612 0.01792 -0.0765 1.0000 0.0581
-4.000 -0.2059 0.02439 0.01593 -0.0767 1.0000 0.0581
-3.750 -0.1793 0.02307 0.01443 -0.0767 1.0000 0.0595
-3.500 -0.1535 0.02166 0.01313 -0.0769 1.0000 0.0644
-3.250 -0.1279 0.02084 0.01227 -0.0767 1.0000 0.0686
-3.000 -0.1013 0.02005 0.01148 -0.0768 1.0000 0.0738
-2.750 -0.0729 0.01934 0.01082 -0.0776 0.9999 0.0896
-2.500 -0.0245 0.01765 0.01070 -0.0824 0.9960 0.4388
-2.250 0.0134 0.01869 0.01180 -0.0840 0.9872 0.5231
-2.000 0.0481 0.01951 0.01274 -0.0846 0.9783 0.5737
-1.750 0.0899 0.01977 0.01288 -0.0874 0.9705 0.5982
-1.500 0.1257 0.01991 0.01294 -0.0890 0.9609 0.6195
-1.250 0.1673 0.02005 0.01300 -0.0917 0.9530 0.6411
-1.000 0.2044 0.02008 0.01301 -0.0935 0.9434 0.6604
-0.750 0.2408 0.02011 0.01299 -0.0952 0.9335 0.6800
-0.500 0.2857 0.02004 0.01290 -0.0983 0.9263 0.7002
-0.250 0.3180 0.01998 0.01285 -0.0992 0.9149 0.7190
0.000 0.3544 0.01989 0.01277 -0.1007 0.9049 0.7407
0.250 0.3986 0.01961 0.01254 -0.1033 0.8977 0.7631
0.500 0.4310 0.01946 0.01243 -0.1039 0.8863 0.7872
0.750 0.4667 0.01919 0.01223 -0.1049 0.8765 0.8153
1.000 0.5056 0.01865 0.01181 -0.1060 0.8690 0.8499
1.250 0.5312 0.01817 0.01152 -0.1047 0.8570 0.9084
1.500 0.5788 0.01784 0.01117 -0.1086 0.8460 1.0000
1.750 0.6284 0.01742 0.01069 -0.1123 0.8381 1.0000
2.000 0.6657 0.01723 0.01045 -0.1137 0.8256 1.0000
2.250 0.6999 0.01705 0.01024 -0.1143 0.8122 1.0000
2.500 0.7329 0.01686 0.01002 -0.1146 0.7984 1.0000
2.750 0.7650 0.01666 0.00983 -0.1145 0.7841 1.0000
3.000 0.7964 0.01645 0.00960 -0.1143 0.7689 1.0000
3.250 0.8272 0.01623 0.00936 -0.1138 0.7528 1.0000
3.500 0.8548 0.01616 0.00928 -0.1130 0.7333 1.0000
3.750 0.8829 0.01603 0.00915 -0.1121 0.7126 1.0000
4.000 0.9104 0.01592 0.00900 -0.1111 0.6900 1.0000
4.250 0.9374 0.01587 0.00888 -0.1100 0.6659 1.0000
4.500 0.9627 0.01595 0.00896 -0.1088 0.6393 1.0000
4.750 0.9878 0.01609 0.00906 -0.1077 0.6120 1.0000
5.000 1.0124 0.01629 0.00920 -0.1066 0.5833 1.0000
5.250 1.0362 0.01655 0.00940 -0.1053 0.5526 1.0000
5.500 1.0594 0.01688 0.00966 -0.1040 0.5203 1.0000
5.750 1.0813 0.01729 0.01002 -0.1027 0.4840 1.0000
6.000 1.1021 0.01780 0.01040 -0.1011 0.4447 1.0000
6.250 1.1209 0.01843 0.01089 -0.0994 0.3979 1.0000
6.500 1.1375 0.01932 0.01152 -0.0975 0.3451 1.0000
6.750 1.1525 0.02050 0.01238 -0.0954 0.2898 1.0000
7.000 1.1674 0.02193 0.01343 -0.0935 0.2455 1.0000
7.250 1.1843 0.02335 0.01459 -0.0920 0.2142 1.0000
7.500 1.2036 0.02469 0.01582 -0.0907 0.1919 1.0000
7.750 1.2242 0.02610 0.01710 -0.0897 0.1757 1.0000
8.000 1.2457 0.02747 0.01845 -0.0889 0.1618 1.0000
8.250 1.2682 0.02892 0.01995 -0.0881 0.1503 1.0000
8.500 1.2912 0.03051 0.02160 -0.0874 0.1404 1.0000
8.750 1.3148 0.03221 0.02322 -0.0870 0.1307 1.0000
9.000 1.3354 0.03368 0.02489 -0.0860 0.1219 1.0000
9.250 1.3555 0.03552 0.02693 -0.0850 0.1131 1.0000
9.500 1.3772 0.03756 0.02890 -0.0846 0.1043 1.0000
9.750 1.3905 0.03900 0.03069 -0.0826 0.0960 1.0000
10.000 1.4056 0.04125 0.03313 -0.0812 0.0879 1.0000
10.250 1.4237 0.04367 0.03542 -0.0806 0.0791 1.0000
10.500 1.4267 0.04542 0.03774 -0.0774 0.0727 1.0000
10.750 1.4399 0.04828 0.04058 -0.0763 0.0662 1.0000
11.000 1.4374 0.05064 0.04348 -0.0728 0.0615 1.0000
11.250 1.4463 0.05244 0.04529 -0.0712 0.0565 1.0000
11.500 1.4421 0.05664 0.04986 -0.0684 0.0540 1.0000
11.750 1.4266 0.05975 0.05342 -0.0644 0.0526 1.0000
12.000 1.4101 0.06321 0.05725 -0.0611 0.0513 1.0000
12.250 1.3931 0.06703 0.06139 -0.0588 0.0503 1.0000
12.500 1.3761 0.07109 0.06573 -0.0574 0.0492 1.0000
12.750 1.3718 0.07400 0.06871 -0.0568 0.0470 1.0000
13.000 1.3716 0.07747 0.07214 -0.0566 0.0449 1.0000
13.250 1.3504 0.08315 0.07808 -0.0570 0.0446 1.0000
13.500 1.3254 0.08913 0.08434 -0.0586 0.0448 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX60-100 10.0% smoothed (fx60100sm-il)