WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.33 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60126-il-1000000.txt Download as CSV file: xf-fx60126-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5596 0.08759 0.08571 -0.0474 1.0000 0.0094
-12.750 -0.5183 0.09342 0.09164 -0.0440 1.0000 0.0098
-12.500 -0.6582 0.05945 0.05704 -0.0663 1.0000 0.0083
-12.250 -0.6726 0.05383 0.05131 -0.0703 1.0000 0.0083
-12.000 -0.6926 0.04789 0.04525 -0.0743 1.0000 0.0082
-11.750 -0.7037 0.04368 0.04094 -0.0769 1.0000 0.0082
-11.500 -0.7192 0.03981 0.03697 -0.0784 1.0000 0.0082
-11.250 -0.7446 0.03729 0.03440 -0.0762 1.0000 0.0082
-11.000 -0.7262 0.03160 0.02843 -0.0880 0.9941 0.0081
-10.750 -0.7000 0.02776 0.02432 -0.0959 0.9884 0.0081
-10.500 -0.6713 0.02506 0.02139 -0.1007 0.9850 0.0081
-10.250 -0.6400 0.02274 0.01885 -0.1048 0.9829 0.0081
-10.000 -0.6120 0.02097 0.01692 -0.1071 0.9775 0.0081
-9.750 -0.5811 0.01961 0.01542 -0.1093 0.9730 0.0082
-9.500 -0.5494 0.01847 0.01415 -0.1114 0.9687 0.0083
-9.250 -0.5234 0.01759 0.01317 -0.1119 0.9604 0.0084
-9.000 -0.4969 0.01649 0.01197 -0.1127 0.9531 0.0084
-8.750 -0.4728 0.01559 0.01096 -0.1126 0.9439 0.0085
-8.500 -0.4477 0.01481 0.01008 -0.1127 0.9360 0.0085
-8.250 -0.4227 0.01402 0.00921 -0.1127 0.9280 0.0086
-8.000 -0.3983 0.01281 0.00787 -0.1130 0.9203 0.0088
-7.750 -0.3723 0.01206 0.00702 -0.1131 0.9125 0.0091
-7.500 -0.3452 0.01151 0.00639 -0.1132 0.9055 0.0094
-7.250 -0.3177 0.01104 0.00587 -0.1134 0.8987 0.0098
-7.000 -0.2900 0.01065 0.00541 -0.1135 0.8927 0.0102
-6.750 -0.2619 0.01028 0.00498 -0.1136 0.8859 0.0107
-6.500 -0.2338 0.00998 0.00460 -0.1137 0.8794 0.0111
-6.250 -0.2055 0.00957 0.00412 -0.1138 0.8726 0.0118
-6.000 -0.1771 0.00925 0.00376 -0.1139 0.8655 0.0129
-5.750 -0.1486 0.00901 0.00345 -0.1140 0.8588 0.0142
-5.500 -0.1199 0.00849 0.00302 -0.1144 0.8517 0.0332
-5.250 -0.0913 0.00817 0.00274 -0.1146 0.8456 0.0502
-5.000 -0.0623 0.00790 0.00253 -0.1149 0.8388 0.0700
-4.750 -0.0336 0.00766 0.00232 -0.1150 0.8318 0.0864
-4.500 -0.0047 0.00742 0.00213 -0.1153 0.8243 0.1113
-4.250 0.0241 0.00708 0.00193 -0.1156 0.8166 0.1553
-4.000 0.0532 0.00679 0.00176 -0.1159 0.8089 0.1970
-3.750 0.0821 0.00656 0.00162 -0.1162 0.8009 0.2346
-3.500 0.1112 0.00637 0.00152 -0.1164 0.7925 0.2702
-3.250 0.1399 0.00625 0.00143 -0.1165 0.7835 0.3019
-3.000 0.1690 0.00615 0.00137 -0.1166 0.7737 0.3223
-2.750 0.1978 0.00610 0.00131 -0.1167 0.7640 0.3395
-2.500 0.2264 0.00608 0.00127 -0.1167 0.7522 0.3546
-2.250 0.2549 0.00609 0.00122 -0.1167 0.7370 0.3675
-2.000 0.2833 0.00610 0.00119 -0.1166 0.7203 0.3795
-1.750 0.3118 0.00612 0.00117 -0.1166 0.7036 0.3921
-1.500 0.3402 0.00615 0.00116 -0.1166 0.6882 0.4027
-1.250 0.3686 0.00620 0.00116 -0.1165 0.6723 0.4144
-1.000 0.3970 0.00625 0.00117 -0.1165 0.6566 0.4266
-0.750 0.4253 0.00630 0.00118 -0.1165 0.6408 0.4362
-0.250 0.4819 0.00644 0.00123 -0.1164 0.6097 0.4533
0.000 0.5101 0.00653 0.00126 -0.1163 0.5950 0.4616
0.250 0.5383 0.00661 0.00131 -0.1163 0.5799 0.4723
0.500 0.5665 0.00670 0.00136 -0.1163 0.5648 0.4818
0.750 0.5947 0.00679 0.00142 -0.1162 0.5509 0.4896
1.000 0.6228 0.00688 0.00148 -0.1162 0.5367 0.4973
1.250 0.6508 0.00699 0.00154 -0.1161 0.5209 0.5056
1.500 0.6789 0.00709 0.00161 -0.1161 0.5059 0.5131
1.750 0.7070 0.00719 0.00168 -0.1161 0.4932 0.5214
2.000 0.7350 0.00729 0.00176 -0.1160 0.4809 0.5298
2.250 0.7628 0.00741 0.00185 -0.1159 0.4688 0.5389
2.500 0.7906 0.00753 0.00196 -0.1159 0.4553 0.5483
2.750 0.8184 0.00766 0.00206 -0.1158 0.4401 0.5575
3.000 0.8459 0.00780 0.00217 -0.1157 0.4242 0.5672
3.250 0.8732 0.00797 0.00230 -0.1156 0.4076 0.5764
3.500 0.9004 0.00814 0.00243 -0.1154 0.3903 0.5857
3.750 0.9275 0.00832 0.00257 -0.1153 0.3714 0.5949
4.000 0.9543 0.00853 0.00273 -0.1151 0.3532 0.6043
4.250 0.9810 0.00875 0.00291 -0.1149 0.3351 0.6144
4.500 1.0076 0.00897 0.00309 -0.1147 0.3168 0.6246
4.750 1.0339 0.00921 0.00328 -0.1144 0.2979 0.6358
5.000 1.0602 0.00945 0.00349 -0.1142 0.2817 0.6483
5.250 1.0864 0.00969 0.00371 -0.1139 0.2639 0.6627
5.750 1.1370 0.01033 0.00424 -0.1132 0.2225 0.6968
6.000 1.1611 0.01075 0.00458 -0.1126 0.1928 0.7188
6.250 1.1851 0.01115 0.00493 -0.1121 0.1706 0.7476
6.500 1.2095 0.01145 0.00526 -0.1116 0.1532 0.7877
7.000 1.2512 0.01183 0.00585 -0.1089 0.1290 1.0000
7.250 1.2764 0.01213 0.00615 -0.1085 0.1217 1.0000
7.750 1.3248 0.01290 0.00682 -0.1075 0.1018 1.0000
8.000 1.3485 0.01331 0.00719 -0.1069 0.0946 1.0000
8.250 1.3715 0.01375 0.00759 -0.1062 0.0883 1.0000
8.500 1.3956 0.01407 0.00794 -0.1056 0.0839 1.0000
8.750 1.4187 0.01447 0.00832 -0.1049 0.0767 1.0000
9.000 1.4406 0.01493 0.00875 -0.1041 0.0686 1.0000
9.250 1.4617 0.01545 0.00921 -0.1031 0.0618 1.0000
9.500 1.4824 0.01596 0.00970 -0.1021 0.0582 1.0000
9.750 1.5020 0.01652 0.01025 -0.1009 0.0540 1.0000
10.000 1.5229 0.01694 0.01071 -0.0999 0.0518 1.0000
10.250 1.5437 0.01733 0.01116 -0.0989 0.0496 1.0000
10.500 1.5619 0.01787 0.01170 -0.0975 0.0465 1.0000
10.750 1.5756 0.01851 0.01235 -0.0954 0.0428 1.0000
11.000 1.5923 0.01893 0.01281 -0.0937 0.0411 1.0000
11.250 1.6064 0.01950 0.01339 -0.0917 0.0385 1.0000
11.500 1.6181 0.02022 0.01410 -0.0895 0.0357 1.0000
11.750 1.6313 0.02089 0.01481 -0.0875 0.0340 1.0000
12.000 1.6438 0.02161 0.01556 -0.0856 0.0323 1.0000
12.250 1.6546 0.02248 0.01644 -0.0836 0.0306 1.0000
12.500 1.6639 0.02348 0.01747 -0.0815 0.0286 1.0000
12.750 1.6754 0.02438 0.01843 -0.0798 0.0278 1.0000
13.000 1.6874 0.02528 0.01939 -0.0783 0.0270 1.0000
13.250 1.6977 0.02632 0.02049 -0.0767 0.0258 1.0000
13.500 1.7064 0.02754 0.02175 -0.0750 0.0246 1.0000
13.750 1.7128 0.02899 0.02323 -0.0734 0.0230 1.0000
14.000 1.7218 0.03028 0.02459 -0.0720 0.0220 1.0000
14.250 1.7308 0.03162 0.02598 -0.0708 0.0205 1.0000
14.500 1.7348 0.03346 0.02783 -0.0695 0.0183 1.0000
14.750 1.7396 0.03529 0.02971 -0.0683 0.0155 1.0000
15.000 1.7329 0.03835 0.03274 -0.0670 0.0094 1.0000
15.250 1.7247 0.04175 0.03618 -0.0659 0.0067 1.0000
15.500 1.7202 0.04495 0.03947 -0.0653 0.0057 1.0000
15.750 1.7167 0.04819 0.04282 -0.0650 0.0053 1.0000
16.000 1.7115 0.05183 0.04657 -0.0650 0.0049 1.0000
16.250 1.7075 0.05549 0.05034 -0.0652 0.0046 1.0000
16.500 1.7038 0.05926 0.05423 -0.0658 0.0044 1.0000
16.750 1.6996 0.06326 0.05834 -0.0665 0.0043 1.0000
17.000 1.6935 0.06770 0.06290 -0.0676 0.0042 1.0000
17.250 1.6862 0.07244 0.06776 -0.0690 0.0041 1.0000
17.500 1.6769 0.07766 0.07310 -0.0706 0.0040 1.0000
17.750 1.6665 0.08322 0.07879 -0.0726 0.0039 1.0000
18.000 1.6548 0.08916 0.08486 -0.0750 0.0038 1.0000
18.250 1.6417 0.09550 0.09133 -0.0776 0.0038 1.0000
18.500 1.6274 0.10224 0.09821 -0.0806 0.0037 1.0000
18.750 1.6116 0.10942 0.10553 -0.0840 0.0037 1.0000
19.000 1.5957 0.11675 0.11300 -0.0877 0.0036 1.0000
19.250 1.5788 0.12442 0.12081 -0.0917 0.0036 1.0000
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