FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX60-100 10.0% smoothed (fx60100sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.65 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60100sm-il-1000000-n5.txt Download as CSV file: xf-fx60100sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4126 0.08590 0.08424 -0.0392 1.0000 0.0052
-9.250 -0.5121 0.03024 0.02781 -0.0996 0.9723 0.0047
-9.000 -0.4909 0.02425 0.02126 -0.1072 0.9625 0.0047
-8.750 -0.4677 0.02037 0.01689 -0.1107 0.9545 0.0048
-8.500 -0.4455 0.01761 0.01373 -0.1120 0.9458 0.0048
-8.250 -0.4205 0.01577 0.01160 -0.1129 0.9391 0.0049
-8.000 -0.3951 0.01446 0.01010 -0.1133 0.9320 0.0050
-7.750 -0.3685 0.01358 0.00906 -0.1136 0.9259 0.0051
-7.500 -0.3416 0.01290 0.00828 -0.1138 0.9192 0.0053
-7.250 -0.3145 0.01235 0.00763 -0.1139 0.9128 0.0054
-7.000 -0.2870 0.01184 0.00704 -0.1141 0.9063 0.0056
-6.750 -0.2595 0.01135 0.00646 -0.1142 0.8994 0.0058
-6.500 -0.2318 0.01087 0.00589 -0.1144 0.8928 0.0061
-6.250 -0.2039 0.01045 0.00538 -0.1145 0.8854 0.0064
-6.000 -0.1759 0.01005 0.00490 -0.1147 0.8784 0.0066
-5.750 -0.1477 0.00969 0.00446 -0.1148 0.8708 0.0069
-5.500 -0.1195 0.00938 0.00408 -0.1149 0.8636 0.0070
-5.250 -0.0911 0.00900 0.00360 -0.1151 0.8557 0.0073
-5.000 -0.0625 0.00866 0.00320 -0.1153 0.8480 0.0078
-4.750 -0.0342 0.00843 0.00292 -0.1154 0.8398 0.0082
-4.500 -0.0057 0.00823 0.00268 -0.1155 0.8314 0.0089
-4.250 0.0227 0.00808 0.00246 -0.1156 0.8230 0.0097
-4.000 0.0513 0.00788 0.00221 -0.1157 0.8138 0.0107
-3.750 0.0799 0.00770 0.00198 -0.1158 0.8048 0.0122
-3.500 0.1083 0.00758 0.00180 -0.1158 0.7951 0.0137
-3.250 0.1369 0.00745 0.00163 -0.1159 0.7848 0.0161
-3.000 0.1654 0.00734 0.00149 -0.1159 0.7743 0.0199
-2.750 0.1940 0.00717 0.00133 -0.1161 0.7634 0.0375
-2.500 0.2229 0.00673 0.00113 -0.1165 0.7517 0.1267
-2.250 0.2518 0.00632 0.00099 -0.1170 0.7395 0.2229
-2.000 0.2804 0.00613 0.00092 -0.1172 0.7270 0.2816
-1.750 0.3088 0.00602 0.00089 -0.1174 0.7138 0.3292
-1.500 0.3370 0.00596 0.00088 -0.1174 0.6999 0.3648
-1.250 0.3652 0.00598 0.00086 -0.1174 0.6851 0.3792
-1.000 0.3933 0.00603 0.00086 -0.1173 0.6694 0.3909
-0.750 0.4212 0.00608 0.00086 -0.1173 0.6529 0.4040
-0.500 0.4491 0.00615 0.00088 -0.1172 0.6357 0.4163
-0.250 0.4771 0.00621 0.00090 -0.1171 0.6184 0.4272
0.000 0.5050 0.00628 0.00093 -0.1171 0.6011 0.4379
0.500 0.5605 0.00648 0.00102 -0.1169 0.5637 0.4569
0.750 0.5881 0.00659 0.00107 -0.1168 0.5430 0.4660
1.000 0.6156 0.00673 0.00114 -0.1167 0.5217 0.4756
1.250 0.6431 0.00686 0.00121 -0.1166 0.5013 0.4852
1.500 0.6701 0.00704 0.00131 -0.1164 0.4748 0.4945
1.750 0.6969 0.00726 0.00142 -0.1162 0.4423 0.5048
2.000 0.7237 0.00748 0.00154 -0.1160 0.4118 0.5147
2.250 0.7504 0.00770 0.00166 -0.1158 0.3838 0.5248
2.500 0.7772 0.00793 0.00181 -0.1156 0.3564 0.5358
2.750 0.8041 0.00813 0.00194 -0.1155 0.3336 0.5471
3.000 0.8309 0.00833 0.00210 -0.1153 0.3118 0.5587
3.250 0.8572 0.00861 0.00227 -0.1151 0.2830 0.5703
3.500 0.8834 0.00889 0.00247 -0.1149 0.2566 0.5825
3.750 0.9098 0.00914 0.00267 -0.1146 0.2339 0.5959
4.000 0.9360 0.00941 0.00288 -0.1144 0.2117 0.6095
4.250 0.9618 0.00973 0.00311 -0.1141 0.1862 0.6238
4.500 0.9873 0.01008 0.00339 -0.1138 0.1601 0.6395
4.750 1.0132 0.01036 0.00364 -0.1135 0.1416 0.6560
5.000 1.0391 0.01064 0.00390 -0.1132 0.1256 0.6738
5.250 1.0648 0.01093 0.00418 -0.1129 0.1113 0.6953
5.500 1.0904 0.01120 0.00446 -0.1126 0.0987 0.7192
5.750 1.1162 0.01144 0.00474 -0.1123 0.0901 0.7485
6.000 1.1417 0.01164 0.00503 -0.1119 0.0832 0.7906
6.250 1.1615 0.01154 0.00526 -0.1102 0.0776 1.0000
6.500 1.1870 0.01185 0.00555 -0.1098 0.0716 1.0000
6.750 1.2124 0.01216 0.00585 -0.1095 0.0664 1.0000
7.000 1.2379 0.01245 0.00615 -0.1091 0.0624 1.0000
7.250 1.2625 0.01285 0.00650 -0.1087 0.0556 1.0000
7.500 1.2876 0.01315 0.00682 -0.1083 0.0517 1.0000
7.750 1.3116 0.01357 0.00720 -0.1077 0.0453 1.0000
8.000 1.3360 0.01393 0.00755 -0.1073 0.0406 1.0000
8.250 1.3593 0.01440 0.00798 -0.1066 0.0348 1.0000
8.500 1.3832 0.01478 0.00838 -0.1061 0.0315 1.0000
8.750 1.4057 0.01528 0.00886 -0.1054 0.0263 1.0000
9.000 1.4283 0.01578 0.00935 -0.1046 0.0221 1.0000
9.250 1.4499 0.01634 0.00990 -0.1038 0.0177 1.0000
9.500 1.4707 0.01696 0.01051 -0.1028 0.0138 1.0000
9.750 1.4910 0.01760 0.01115 -0.1018 0.0109 1.0000
10.000 1.5114 0.01820 0.01179 -0.1008 0.0089 1.0000
10.250 1.5306 0.01887 0.01249 -0.0996 0.0072 1.0000
10.500 1.5497 0.01951 0.01316 -0.0984 0.0061 1.0000
10.750 1.5673 0.02024 0.01393 -0.0970 0.0051 1.0000
11.000 1.5851 0.02088 0.01463 -0.0956 0.0046 1.0000
11.250 1.6017 0.02158 0.01538 -0.0940 0.0042 1.0000
11.500 1.6148 0.02232 0.01618 -0.0919 0.0038 1.0000
11.750 1.6256 0.02314 0.01706 -0.0895 0.0035 1.0000
12.000 1.6353 0.02404 0.01804 -0.0870 0.0032 1.0000
12.250 1.6460 0.02490 0.01898 -0.0847 0.0031 1.0000
12.500 1.6557 0.02586 0.02002 -0.0825 0.0030 1.0000
12.750 1.6647 0.02691 0.02116 -0.0804 0.0029 1.0000
13.000 1.6728 0.02808 0.02242 -0.0783 0.0028 1.0000
13.250 1.6801 0.02936 0.02379 -0.0763 0.0027 1.0000
13.500 1.6866 0.03076 0.02528 -0.0744 0.0026 1.0000
13.750 1.6922 0.03230 0.02691 -0.0726 0.0025 1.0000
14.000 1.6967 0.03400 0.02871 -0.0709 0.0024 1.0000
14.250 1.7002 0.03588 0.03069 -0.0694 0.0024 1.0000
14.500 1.7024 0.03798 0.03289 -0.0681 0.0023 1.0000
14.750 1.7031 0.04033 0.03535 -0.0669 0.0022 1.0000
15.000 1.7023 0.04295 0.03809 -0.0660 0.0022 1.0000
15.250 1.6996 0.04595 0.04121 -0.0653 0.0021 1.0000
15.500 1.6956 0.04926 0.04465 -0.0650 0.0021 1.0000
15.750 1.6892 0.05307 0.04859 -0.0651 0.0020 1.0000
16.000 1.6808 0.05737 0.05304 -0.0656 0.0020 1.0000
16.250 1.6709 0.06217 0.05799 -0.0666 0.0020 1.0000
16.500 1.6584 0.06770 0.06367 -0.0683 0.0019 1.0000
16.750 1.6444 0.07378 0.06991 -0.0705 0.0019 1.0000
17.000 1.6297 0.08035 0.07663 -0.0733 0.0019 1.0000
17.250 1.6142 0.08737 0.08381 -0.0765 0.0019 1.0000
17.500 1.5948 0.09543 0.09203 -0.0805 0.0019 1.0000
17.750 1.5727 0.10442 0.10119 -0.0852 0.0019 1.0000
18.000 1.5500 0.11384 0.11077 -0.0903 0.0019 1.0000
18.250 1.5230 0.12451 0.12162 -0.0964 0.0019 1.0000
18.500 1.4982 0.13502 0.13229 -0.1026 0.0019 1.0000
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Polar data table (+)
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