FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.06 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60100sm-il-1000000.txt Download as CSV file: xf-fx60100sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2994 0.09393 0.09238 -0.0383 1.0000 0.0108
-10.250 -0.2984 0.09061 0.08907 -0.0387 1.0000 0.0109
-10.000 -0.2977 0.08748 0.08594 -0.0389 1.0000 0.0111
-6.000 -0.1664 0.01299 0.00846 -0.1169 0.9334 0.0094
-5.750 -0.1393 0.01192 0.00725 -0.1168 0.9273 0.0096
-5.500 -0.1119 0.01128 0.00651 -0.1168 0.9207 0.0100
-5.250 -0.0845 0.01026 0.00536 -0.1169 0.9141 0.0105
-5.000 -0.0566 0.00953 0.00457 -0.1171 0.9076 0.0112
-4.750 -0.0285 0.00912 0.00411 -0.1172 0.9007 0.0117
-4.500 -0.0002 0.00875 0.00367 -0.1172 0.8941 0.0123
-4.250 0.0283 0.00840 0.00325 -0.1173 0.8869 0.0130
-4.000 0.0567 0.00819 0.00299 -0.1174 0.8801 0.0139
-3.750 0.0857 0.00771 0.00242 -0.1176 0.8725 0.0161
-3.500 0.1143 0.00749 0.00215 -0.1176 0.8653 0.0184
-3.250 0.1431 0.00724 0.00183 -0.1177 0.8573 0.0226
-3.000 0.1720 0.00693 0.00157 -0.1179 0.8495 0.0465
-2.750 0.2013 0.00600 0.00125 -0.1188 0.8411 0.2341
-2.500 0.2300 0.00569 0.00116 -0.1191 0.8326 0.3180
-2.250 0.2583 0.00558 0.00112 -0.1192 0.8239 0.3608
-2.000 0.2868 0.00552 0.00108 -0.1192 0.8142 0.3852
-1.750 0.3152 0.00548 0.00106 -0.1192 0.8046 0.4087
-1.500 0.3434 0.00548 0.00104 -0.1191 0.7945 0.4292
-1.250 0.3717 0.00547 0.00102 -0.1191 0.7833 0.4410
-1.000 0.4000 0.00548 0.00100 -0.1190 0.7716 0.4520
-0.750 0.4282 0.00550 0.00099 -0.1189 0.7592 0.4640
-0.500 0.4563 0.00553 0.00099 -0.1188 0.7461 0.4757
-0.250 0.4843 0.00556 0.00099 -0.1187 0.7324 0.4869
0.000 0.5123 0.00560 0.00101 -0.1186 0.7181 0.4982
0.250 0.5402 0.00566 0.00103 -0.1185 0.7030 0.5091
0.500 0.5680 0.00572 0.00105 -0.1184 0.6863 0.5202
0.750 0.5957 0.00580 0.00110 -0.1183 0.6682 0.5316
1.000 0.6232 0.00589 0.00114 -0.1181 0.6498 0.5430
1.250 0.6508 0.00598 0.00120 -0.1180 0.6302 0.5551
1.500 0.6779 0.00612 0.00127 -0.1178 0.6062 0.5675
1.750 0.7048 0.00628 0.00135 -0.1175 0.5783 0.5806
2.000 0.7318 0.00644 0.00144 -0.1173 0.5514 0.5941
2.250 0.7588 0.00660 0.00155 -0.1171 0.5259 0.6083
2.500 0.7857 0.00678 0.00167 -0.1169 0.5011 0.6234
2.750 0.8127 0.00693 0.00179 -0.1168 0.4789 0.6393
3.000 0.8397 0.00710 0.00192 -0.1166 0.4564 0.6565
3.250 0.8662 0.00730 0.00207 -0.1163 0.4298 0.6753
3.500 0.8928 0.00751 0.00224 -0.1161 0.4044 0.6962
3.750 0.9193 0.00770 0.00241 -0.1159 0.3799 0.7205
4.000 0.9454 0.00791 0.00260 -0.1156 0.3541 0.7493
4.250 0.9709 0.00814 0.00282 -0.1152 0.3237 0.7880
4.500 0.9935 0.00828 0.00305 -0.1142 0.2918 0.8736
4.750 1.0157 0.00846 0.00323 -0.1130 0.2627 1.0000
5.000 1.0410 0.00887 0.00349 -0.1126 0.2320 1.0000
5.250 1.0659 0.00933 0.00379 -0.1122 0.1998 1.0000
5.500 1.0905 0.00981 0.00411 -0.1118 0.1680 1.0000
5.750 1.1153 0.01026 0.00443 -0.1114 0.1429 1.0000
6.000 1.1401 0.01069 0.00476 -0.1110 0.1228 1.0000
6.250 1.1649 0.01112 0.00510 -0.1105 0.1068 1.0000
6.500 1.1899 0.01151 0.00544 -0.1101 0.0950 1.0000
6.750 1.2152 0.01185 0.00576 -0.1097 0.0871 1.0000
7.000 1.2398 0.01225 0.00613 -0.1093 0.0786 1.0000
7.250 1.2648 0.01258 0.00645 -0.1089 0.0728 1.0000
7.500 1.2892 0.01298 0.00684 -0.1084 0.0662 1.0000
7.750 1.3142 0.01330 0.00715 -0.1080 0.0616 1.0000
8.000 1.3378 0.01376 0.00757 -0.1074 0.0550 1.0000
8.250 1.3627 0.01404 0.00789 -0.1069 0.0521 1.0000
8.500 1.3862 0.01446 0.00830 -0.1064 0.0476 1.0000
8.750 1.4098 0.01487 0.00872 -0.1058 0.0435 1.0000
9.000 1.4332 0.01526 0.00913 -0.1051 0.0396 1.0000
9.250 1.4554 0.01578 0.00961 -0.1044 0.0344 1.0000
9.500 1.4776 0.01626 0.01009 -0.1036 0.0298 1.0000
9.750 1.4984 0.01685 0.01067 -0.1026 0.0241 1.0000
10.000 1.5175 0.01760 0.01138 -0.1014 0.0178 1.0000
10.250 1.5355 0.01842 0.01219 -0.1001 0.0129 1.0000
10.500 1.5525 0.01929 0.01308 -0.0986 0.0099 1.0000
10.750 1.5690 0.02015 0.01396 -0.0970 0.0082 1.0000
11.000 1.5841 0.02107 0.01496 -0.0952 0.0070 1.0000
11.250 1.5994 0.02183 0.01580 -0.0934 0.0064 1.0000
11.500 1.6108 0.02268 0.01671 -0.0910 0.0059 1.0000
11.750 1.6184 0.02372 0.01782 -0.0881 0.0055 1.0000
12.000 1.6204 0.02518 0.01942 -0.0846 0.0050 1.0000
12.250 1.6294 0.02619 0.02053 -0.0823 0.0049 1.0000
12.500 1.6374 0.02733 0.02176 -0.0800 0.0048 1.0000
12.750 1.6441 0.02860 0.02314 -0.0778 0.0046 1.0000
13.000 1.6493 0.03006 0.02469 -0.0756 0.0045 1.0000
13.250 1.6539 0.03163 0.02637 -0.0736 0.0044 1.0000
13.500 1.6570 0.03342 0.02827 -0.0717 0.0043 1.0000
13.750 1.6596 0.03534 0.03029 -0.0700 0.0042 1.0000
14.000 1.6607 0.03751 0.03258 -0.0685 0.0041 1.0000
14.250 1.6608 0.03988 0.03506 -0.0672 0.0040 1.0000
14.500 1.6591 0.04259 0.03788 -0.0662 0.0039 1.0000
14.750 1.6561 0.04562 0.04103 -0.0655 0.0038 1.0000
15.000 1.6510 0.04906 0.04460 -0.0652 0.0038 1.0000
15.250 1.6434 0.05305 0.04874 -0.0653 0.0037 1.0000
15.500 1.6341 0.05752 0.05335 -0.0660 0.0036 1.0000
15.750 1.6221 0.06270 0.05868 -0.0672 0.0036 1.0000
16.000 1.6088 0.06847 0.06460 -0.0690 0.0035 1.0000
16.250 1.5936 0.07491 0.07120 -0.0715 0.0035 1.0000
16.500 1.5771 0.08194 0.07838 -0.0746 0.0035 1.0000
16.750 1.5592 0.08961 0.08621 -0.0782 0.0035 1.0000
17.000 1.5405 0.09774 0.09450 -0.0823 0.0035 1.0000
17.250 1.5204 0.10649 0.10340 -0.0869 0.0035 1.0000
17.500 1.5016 0.11520 0.11227 -0.0916 0.0035 1.0000
17.750 1.4833 0.12405 0.12125 -0.0965 0.0035 1.0000
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Polar data table (+)
Polar graphs
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