WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 100,000 Max Cl/Cd: 59.42 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601261-il-100000.txt Download as CSV file: xf-fx601261-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 60-126/1 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3070 0.09639 0.09192 -0.0377 1.0000 0.1240
-8.000 -0.3180 0.09449 0.09015 -0.0369 1.0000 0.1280
-7.750 -0.3923 0.09651 0.09248 -0.0347 1.0000 0.1313
-7.500 -0.3825 0.09279 0.08880 -0.0317 1.0000 0.1327
-7.250 -0.3790 0.09075 0.08681 -0.0282 1.0000 0.1341
-7.000 -0.3884 0.08945 0.08558 -0.0247 1.0000 0.1356
-6.750 -0.4037 0.08843 0.08465 -0.0214 1.0000 0.1373
-6.500 -0.4221 0.08733 0.08364 -0.0186 1.0000 0.1395
-6.000 -0.4371 0.05834 0.05431 -0.0590 0.9895 0.0927
-5.750 -0.3877 0.03884 0.03271 -0.0791 0.9855 0.0479
-5.500 -0.3457 0.03431 0.02747 -0.0840 0.9807 0.0443
-5.250 -0.3016 0.03117 0.02355 -0.0876 0.9754 0.0417
-5.000 -0.2587 0.02914 0.02121 -0.0907 0.9707 0.0415
-4.750 -0.2231 0.02749 0.01950 -0.0927 0.9639 0.0437
-4.500 -0.1798 0.02619 0.01809 -0.0957 0.9592 0.0462
-4.250 -0.1462 0.02508 0.01694 -0.0968 0.9516 0.0480
-4.000 -0.1027 0.02409 0.01587 -0.0997 0.9463 0.0502
-3.750 -0.0653 0.02309 0.01482 -0.1021 0.9387 0.0551
-3.500 -0.0188 0.02203 0.01370 -0.1059 0.9329 0.0717
-3.250 0.0265 0.02023 0.01329 -0.1107 0.9272 0.3586
-3.000 0.0643 0.02085 0.01398 -0.1119 0.9185 0.4374
-2.750 0.0963 0.02153 0.01464 -0.1120 0.9092 0.4786
-2.500 0.1340 0.02224 0.01544 -0.1124 0.9025 0.5195
-2.250 0.1616 0.02257 0.01578 -0.1116 0.8929 0.5420
-2.000 0.2070 0.02234 0.01542 -0.1144 0.8878 0.5591
-1.750 0.2383 0.02234 0.01535 -0.1148 0.8786 0.5747
-1.500 0.2824 0.02206 0.01498 -0.1172 0.8731 0.5911
-1.250 0.3145 0.02194 0.01479 -0.1178 0.8636 0.6042
-1.000 0.3573 0.02156 0.01433 -0.1200 0.8574 0.6191
-0.750 0.3867 0.02149 0.01422 -0.1200 0.8470 0.6326
-0.500 0.4287 0.02108 0.01375 -0.1219 0.8411 0.6469
-0.250 0.4556 0.02110 0.01372 -0.1217 0.8300 0.6595
0.000 0.4895 0.02088 0.01349 -0.1223 0.8222 0.6719
0.250 0.5192 0.02074 0.01335 -0.1222 0.8126 0.6839
0.500 0.5463 0.02068 0.01330 -0.1217 0.8017 0.6968
0.750 0.5832 0.02026 0.01285 -0.1224 0.7946 0.7115
1.000 0.6074 0.02025 0.01287 -0.1214 0.7823 0.7254
1.250 0.6333 0.02021 0.01285 -0.1207 0.7711 0.7397
1.500 0.6653 0.01993 0.01257 -0.1207 0.7630 0.7553
1.750 0.6904 0.01988 0.01257 -0.1199 0.7518 0.7718
2.000 0.7148 0.01986 0.01261 -0.1189 0.7404 0.7901
2.250 0.7420 0.01964 0.01241 -0.1181 0.7302 0.8112
2.500 0.7684 0.01927 0.01209 -0.1169 0.7202 0.8365
2.750 0.7869 0.01910 0.01204 -0.1145 0.7078 0.8697
3.250 0.8509 0.01873 0.01174 -0.1159 0.6840 1.0000
3.500 0.8884 0.01869 0.01157 -0.1177 0.6723 1.0000
3.750 0.9223 0.01866 0.01145 -0.1185 0.6597 1.0000
4.000 0.9518 0.01873 0.01144 -0.1186 0.6452 1.0000
4.250 0.9806 0.01879 0.01143 -0.1185 0.6305 1.0000
4.500 1.0090 0.01884 0.01143 -0.1181 0.6153 1.0000
4.750 1.0371 0.01887 0.01139 -0.1177 0.5995 1.0000
5.000 1.0624 0.01903 0.01152 -0.1170 0.5824 1.0000
5.250 1.0878 0.01921 0.01170 -0.1162 0.5657 1.0000
5.500 1.1133 0.01943 0.01191 -0.1155 0.5493 1.0000
5.750 1.1382 0.01966 0.01212 -0.1147 0.5321 1.0000
6.000 1.1628 0.01988 0.01233 -0.1138 0.5141 1.0000
6.250 1.1873 0.02010 0.01247 -0.1129 0.4956 1.0000
6.500 1.2093 0.02040 0.01278 -0.1117 0.4754 1.0000
6.750 1.2307 0.02073 0.01312 -0.1104 0.4544 1.0000
7.000 1.2526 0.02108 0.01340 -0.1091 0.4340 1.0000
7.250 1.2715 0.02153 0.01389 -0.1075 0.4109 1.0000
7.500 1.2902 0.02202 0.01430 -0.1059 0.3873 1.0000
7.750 1.3066 0.02259 0.01482 -0.1040 0.3617 1.0000
8.000 1.3217 0.02329 0.01549 -0.1019 0.3354 1.0000
8.250 1.3358 0.02411 0.01623 -0.0998 0.3098 1.0000
8.500 1.3491 0.02507 0.01702 -0.0976 0.2863 1.0000
8.750 1.3616 0.02613 0.01805 -0.0955 0.2633 1.0000
9.000 1.3742 0.02726 0.01907 -0.0934 0.2442 1.0000
9.250 1.3872 0.02850 0.02017 -0.0914 0.2273 1.0000
9.500 1.3991 0.02974 0.02138 -0.0894 0.2116 1.0000
9.750 1.4104 0.03097 0.02256 -0.0872 0.1981 1.0000
10.000 1.4209 0.03221 0.02383 -0.0850 0.1860 1.0000
10.250 1.4330 0.03360 0.02527 -0.0831 0.1750 1.0000
10.500 1.4472 0.03513 0.02681 -0.0816 0.1650 1.0000
10.750 1.4646 0.03668 0.02826 -0.0806 0.1554 1.0000
11.000 1.4708 0.03813 0.02994 -0.0781 0.1472 1.0000
11.250 1.4848 0.03981 0.03161 -0.0768 0.1391 1.0000
11.500 1.4930 0.04137 0.03325 -0.0749 0.1316 1.0000
11.750 1.5040 0.04330 0.03526 -0.0734 0.1245 1.0000
12.000 1.5100 0.04500 0.03707 -0.0715 0.1182 1.0000
12.250 1.5201 0.04695 0.03905 -0.0702 0.1122 1.0000
12.500 1.5182 0.04892 0.04128 -0.0680 0.1075 1.0000
12.750 1.5291 0.05045 0.04270 -0.0670 0.1021 1.0000
13.000 1.5283 0.05288 0.04541 -0.0653 0.0986 1.0000
13.250 1.5262 0.05531 0.04810 -0.0638 0.0953 1.0000
13.500 1.5311 0.05738 0.05025 -0.0628 0.0919 1.0000
13.750 1.5508 0.05941 0.05218 -0.0625 0.0881 1.0000
14.000 1.5424 0.06252 0.05565 -0.0612 0.0866 1.0000
14.250 1.5340 0.06587 0.05932 -0.0603 0.0847 1.0000
14.500 1.5251 0.06938 0.06312 -0.0597 0.0828 1.0000
14.750 1.5183 0.07272 0.06665 -0.0596 0.0806 1.0000
15.000 1.5208 0.07509 0.06904 -0.0595 0.0779 1.0000
15.250 1.5303 0.07758 0.07152 -0.0593 0.0754 1.0000
15.500 1.5135 0.08250 0.07679 -0.0600 0.0747 1.0000
15.750 1.4949 0.08801 0.08262 -0.0613 0.0740 1.0000
16.000 1.4739 0.09423 0.08916 -0.0633 0.0734 1.0000
16.250 1.4500 0.10138 0.09660 -0.0661 0.0732 1.0000
16.500 1.4203 0.11000 0.10552 -0.0703 0.0732 1.0000
16.750 1.3833 0.12069 0.11648 -0.0764 0.0738 1.0000
17.000 1.3411 0.13366 0.12966 -0.0843 0.0750 1.0000
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Polar data table (+)
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