FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.35 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601001-il-1000000-n5.txt Download as CSV file: xf-fx601001-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-100 (126) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6633 0.05524 0.05341 -0.0564 1.0000 0.0029
-11.000 -0.7068 0.04477 0.04278 -0.0624 1.0000 0.0029
-10.750 -0.7186 0.03883 0.03672 -0.0685 0.9978 0.0028
-10.500 -0.6921 0.02827 0.02565 -0.0914 0.9898 0.0029
-10.250 -0.6624 0.02457 0.02163 -0.0984 0.9869 0.0030
-10.000 -0.6335 0.02257 0.01944 -0.1018 0.9833 0.0031
-9.750 -0.6023 0.02101 0.01772 -0.1047 0.9798 0.0031
-9.500 -0.5694 0.01967 0.01624 -0.1076 0.9768 0.0032
-9.250 -0.5404 0.01872 0.01518 -0.1090 0.9706 0.0034
-9.000 -0.5089 0.01751 0.01381 -0.1111 0.9654 0.0035
-8.750 -0.4813 0.01646 0.01260 -0.1120 0.9573 0.0036
-8.500 -0.4532 0.01534 0.01128 -0.1131 0.9511 0.0038
-8.250 -0.4263 0.01439 0.01018 -0.1136 0.9437 0.0039
-8.000 -0.3988 0.01353 0.00917 -0.1141 0.9372 0.0041
-7.750 -0.3717 0.01283 0.00836 -0.1144 0.9295 0.0042
-7.500 -0.3442 0.01225 0.00765 -0.1146 0.9223 0.0044
-7.250 -0.3167 0.01173 0.00704 -0.1148 0.9136 0.0045
-7.000 -0.2892 0.01096 0.00612 -0.1151 0.9044 0.0048
-6.750 -0.2615 0.01039 0.00544 -0.1154 0.8944 0.0051
-6.500 -0.2338 0.01000 0.00497 -0.1155 0.8836 0.0054
-6.250 -0.2058 0.00967 0.00454 -0.1156 0.8732 0.0057
-6.000 -0.1778 0.00936 0.00414 -0.1157 0.8634 0.0061
-5.750 -0.1497 0.00911 0.00381 -0.1158 0.8536 0.0067
-5.500 -0.1215 0.00890 0.00353 -0.1159 0.8438 0.0072
-5.250 -0.0930 0.00857 0.00309 -0.1161 0.8343 0.0079
-5.000 -0.0646 0.00831 0.00274 -0.1162 0.8247 0.0091
-4.750 -0.0361 0.00811 0.00246 -0.1163 0.8148 0.0104
-4.500 -0.0076 0.00795 0.00223 -0.1164 0.8058 0.0117
-4.250 0.0209 0.00780 0.00203 -0.1165 0.7970 0.0182
-4.000 0.0496 0.00756 0.00185 -0.1168 0.7880 0.0367
-3.750 0.0781 0.00744 0.00171 -0.1169 0.7787 0.0455
-3.500 0.1064 0.00737 0.00159 -0.1170 0.7684 0.0516
-3.250 0.1350 0.00725 0.00147 -0.1171 0.7576 0.0606
-3.000 0.1635 0.00715 0.00135 -0.1172 0.7472 0.0724
-2.750 0.1922 0.00693 0.00121 -0.1175 0.7357 0.1124
-2.250 0.2492 0.00655 0.00100 -0.1180 0.7068 0.2110
-2.000 0.2774 0.00644 0.00093 -0.1181 0.6864 0.2535
-1.750 0.3054 0.00628 0.00084 -0.1183 0.6635 0.3143
-1.500 0.3333 0.00616 0.00082 -0.1184 0.6409 0.3833
-1.250 0.3612 0.00620 0.00086 -0.1184 0.6217 0.4205
-1.000 0.3891 0.00628 0.00090 -0.1184 0.6049 0.4376
-0.750 0.4171 0.00638 0.00093 -0.1183 0.5897 0.4509
-0.500 0.4452 0.00647 0.00097 -0.1183 0.5771 0.4592
-0.250 0.4732 0.00657 0.00102 -0.1182 0.5633 0.4678
0.000 0.5011 0.00668 0.00107 -0.1182 0.5496 0.4742
0.250 0.5292 0.00678 0.00111 -0.1181 0.5368 0.4775
0.500 0.5573 0.00685 0.00115 -0.1181 0.5253 0.4804
0.750 0.5854 0.00692 0.00120 -0.1181 0.5164 0.4831
1.000 0.6135 0.00699 0.00125 -0.1181 0.5077 0.4855
1.250 0.6417 0.00706 0.00130 -0.1181 0.4990 0.4879
1.500 0.6696 0.00716 0.00136 -0.1180 0.4888 0.4905
1.750 0.6974 0.00727 0.00143 -0.1180 0.4750 0.4926
2.000 0.7250 0.00738 0.00150 -0.1179 0.4559 0.4949
2.250 0.7523 0.00755 0.00160 -0.1178 0.4326 0.4974
2.500 0.7791 0.00777 0.00172 -0.1176 0.4050 0.4996
2.750 0.8057 0.00802 0.00186 -0.1174 0.3769 0.5014
3.000 0.8324 0.00825 0.00202 -0.1173 0.3520 0.5029
3.250 0.8588 0.00853 0.00219 -0.1170 0.3258 0.5043
3.500 0.8853 0.00879 0.00237 -0.1168 0.3032 0.5056
3.750 0.9121 0.00901 0.00254 -0.1167 0.2857 0.5071
4.000 0.9385 0.00926 0.00273 -0.1165 0.2638 0.5089
4.250 0.9640 0.00964 0.00297 -0.1161 0.2311 0.5106
4.500 0.9881 0.01019 0.00329 -0.1157 0.1837 0.5122
4.750 1.0134 0.01058 0.00357 -0.1153 0.1580 0.5138
5.000 1.0391 0.01091 0.00384 -0.1150 0.1390 0.5154
5.250 1.0628 0.01148 0.00420 -0.1145 0.0991 0.5173
5.500 1.0860 0.01212 0.00466 -0.1138 0.0637 0.5191
6.000 1.1324 0.01338 0.00566 -0.1125 0.0145 0.5226
6.250 1.1577 0.01371 0.00602 -0.1121 0.0099 0.5246
6.500 1.1827 0.01405 0.00642 -0.1117 0.0085 0.5268
6.750 1.2070 0.01447 0.00688 -0.1111 0.0071 0.5291
7.000 1.2313 0.01488 0.00734 -0.1106 0.0063 0.5318
7.250 1.2559 0.01525 0.00776 -0.1101 0.0058 0.5346
7.500 1.2801 0.01565 0.00820 -0.1096 0.0052 0.5378
7.750 1.3036 0.01611 0.00871 -0.1090 0.0046 0.5413
8.000 1.3259 0.01672 0.00939 -0.1082 0.0041 0.5451
8.500 1.3714 0.01770 0.01051 -0.1067 0.0038 0.5553
8.750 1.3934 0.01824 0.01114 -0.1059 0.0035 0.5628
9.000 1.4148 0.01881 0.01183 -0.1050 0.0033 0.5749
9.250 1.4358 0.01939 0.01253 -0.1041 0.0032 0.5981
9.500 1.4565 0.01996 0.01327 -0.1032 0.0030 0.6522
9.750 1.4763 0.02057 0.01406 -0.1022 0.0028 0.7147
10.000 1.4941 0.02129 0.01500 -0.1010 0.0027 0.7883
10.250 1.5032 0.02200 0.01610 -0.0979 0.0025 1.0000
10.500 1.5204 0.02271 0.01687 -0.0965 0.0024 1.0000
10.750 1.5352 0.02350 0.01774 -0.0947 0.0023 1.0000
11.000 1.5460 0.02435 0.01867 -0.0923 0.0023 1.0000
11.250 1.5547 0.02530 0.01972 -0.0896 0.0022 1.0000
11.500 1.5620 0.02639 0.02090 -0.0870 0.0021 1.0000
11.750 1.5687 0.02757 0.02218 -0.0845 0.0021 1.0000
12.000 1.5744 0.02891 0.02361 -0.0821 0.0020 1.0000
12.250 1.5798 0.03035 0.02515 -0.0799 0.0020 1.0000
12.500 1.5843 0.03193 0.02684 -0.0779 0.0019 1.0000
12.750 1.5881 0.03368 0.02869 -0.0761 0.0019 1.0000
13.000 1.5902 0.03568 0.03079 -0.0744 0.0018 1.0000
13.250 1.5929 0.03775 0.03297 -0.0731 0.0018 1.0000
13.500 1.5932 0.04017 0.03552 -0.0719 0.0017 1.0000
13.750 1.5931 0.04279 0.03824 -0.0711 0.0017 1.0000
14.000 1.5920 0.04567 0.04124 -0.0705 0.0017 1.0000
14.250 1.5896 0.04886 0.04455 -0.0703 0.0017 1.0000
14.500 1.5862 0.05237 0.04818 -0.0704 0.0016 1.0000
14.750 1.5810 0.05630 0.05223 -0.0709 0.0016 1.0000
15.000 1.5735 0.06080 0.05687 -0.0718 0.0016 1.0000
15.250 1.5661 0.06553 0.06173 -0.0731 0.0016 1.0000
15.500 1.5557 0.07096 0.06730 -0.0748 0.0016 1.0000
15.750 1.5437 0.07693 0.07341 -0.0771 0.0015 1.0000
16.000 1.5306 0.08341 0.08003 -0.0798 0.0015 1.0000
16.250 1.5154 0.09050 0.08728 -0.0830 0.0015 1.0000
16.500 1.4990 0.09824 0.09517 -0.0867 0.0015 1.0000
16.750 1.4826 0.10630 0.10337 -0.0909 0.0015 1.0000
17.000 1.4656 0.11471 0.11193 -0.0953 0.0015 1.0000
17.250 1.4482 0.12346 0.12082 -0.1001 0.0015 1.0000
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