WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.27 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx601261-il-1000000.txt Download as CSV file: xf-fx601261-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2522 0.08193 0.08046 -0.0494 0.9975 0.0098
-9.750 -0.2523 0.07490 0.07344 -0.0535 0.9947 0.0099
-9.500 -0.2571 0.06717 0.06572 -0.0576 0.9906 0.0101
-9.250 -0.3155 0.04457 0.04301 -0.0694 0.9855 0.0094
-9.000 -0.3539 0.03034 0.02851 -0.0841 0.9621 0.0091
-8.750 -0.3427 0.02139 0.01920 -0.1058 0.9423 0.0091
-8.500 -0.3116 0.01696 0.01440 -0.1188 0.9218 0.0094
-8.250 -0.2936 0.01451 0.01164 -0.1223 0.8990 0.0097
-8.000 -0.2788 0.01276 0.00961 -0.1233 0.8834 0.0102
-7.750 -0.2640 0.02440 0.02082 -0.1309 0.8982 0.0109
-7.500 -0.2457 0.02176 0.01758 -0.1319 0.8825 0.0117
-7.250 -0.2225 0.02007 0.01589 -0.1320 0.8722 0.0122
-7.000 -0.1985 0.01892 0.01464 -0.1321 0.8628 0.0127
-6.750 -0.1734 0.01802 0.01357 -0.1321 0.8544 0.0136
-6.500 -0.1449 0.01899 0.01431 -0.1319 0.8458 0.0148
-6.250 -0.1232 0.01573 0.01095 -0.1321 0.8382 0.0163
-6.000 -0.0970 0.01498 0.01016 -0.1320 0.8304 0.0175
-5.000 0.0127 0.01157 0.00617 -0.1304 0.8023 0.0116
-4.750 0.0400 0.01055 0.00508 -0.1303 0.7956 0.0089
-4.500 0.0683 0.01033 0.00481 -0.1302 0.7887 0.0085
-4.250 0.0964 0.00983 0.00425 -0.1303 0.7815 0.0083
-4.000 0.1250 0.00929 0.00366 -0.1306 0.7740 0.0082
-3.750 0.1536 0.00895 0.00324 -0.1306 0.7661 0.0083
-3.500 0.1826 0.00848 0.00268 -0.1309 0.7583 0.0088
-3.250 0.2112 0.00823 0.00235 -0.1309 0.7504 0.0098
-3.000 0.2400 0.00807 0.00214 -0.1310 0.7422 0.0105
-2.750 0.2683 0.00797 0.00197 -0.1309 0.7339 0.0111
-2.500 0.2971 0.00784 0.00181 -0.1310 0.7250 0.0131
-2.250 0.3257 0.00766 0.00163 -0.1310 0.7164 0.0401
-2.000 0.3553 0.00688 0.00135 -0.1319 0.7067 0.2049
-1.750 0.3842 0.00646 0.00127 -0.1324 0.6971 0.3184
-1.500 0.4125 0.00637 0.00126 -0.1325 0.6867 0.3636
-1.250 0.4406 0.00638 0.00125 -0.1324 0.6754 0.3841
-1.000 0.4683 0.00639 0.00128 -0.1322 0.6600 0.4143
-0.750 0.4958 0.00645 0.00129 -0.1320 0.6418 0.4284
-0.500 0.5235 0.00651 0.00130 -0.1318 0.6249 0.4378
0.000 0.5790 0.00665 0.00135 -0.1315 0.5981 0.4542
0.250 0.6067 0.00673 0.00139 -0.1314 0.5832 0.4645
0.500 0.6344 0.00682 0.00143 -0.1312 0.5691 0.4750
0.750 0.6623 0.00688 0.00148 -0.1311 0.5566 0.4837
1.000 0.6901 0.00697 0.00154 -0.1310 0.5444 0.4928
1.250 0.7177 0.00706 0.00160 -0.1308 0.5315 0.5024
1.500 0.7450 0.00718 0.00167 -0.1306 0.5151 0.5099
1.750 0.7718 0.00733 0.00176 -0.1304 0.4950 0.5174
2.000 0.7988 0.00748 0.00184 -0.1301 0.4761 0.5249
2.250 0.8260 0.00761 0.00194 -0.1299 0.4604 0.5334
2.500 0.8530 0.00776 0.00204 -0.1297 0.4422 0.5418
2.750 0.8798 0.00792 0.00215 -0.1295 0.4251 0.5513
3.000 0.9066 0.00809 0.00228 -0.1292 0.4089 0.5608
3.250 0.9331 0.00827 0.00242 -0.1289 0.3914 0.5705
3.500 0.9594 0.00848 0.00257 -0.1286 0.3705 0.5805
3.750 0.9854 0.00871 0.00273 -0.1283 0.3500 0.5909
4.000 1.0115 0.00893 0.00290 -0.1279 0.3322 0.6021
4.250 1.0373 0.00917 0.00309 -0.1276 0.3121 0.6142
4.500 1.0628 0.00943 0.00330 -0.1272 0.2915 0.6270
4.750 1.0882 0.00970 0.00352 -0.1268 0.2725 0.6410
5.000 1.1133 0.00999 0.00376 -0.1263 0.2505 0.6581
5.250 1.1379 0.01031 0.00403 -0.1258 0.2293 0.6799
5.500 1.1626 0.01059 0.00432 -0.1253 0.2103 0.7086
5.750 1.1861 0.01097 0.00466 -0.1246 0.1848 0.7486
6.000 1.2096 0.01122 0.00499 -0.1239 0.1680 0.8102
6.250 1.2257 0.01127 0.00524 -0.1214 0.1498 1.0000
6.500 1.2496 0.01168 0.00556 -0.1208 0.1353 1.0000
6.750 1.2734 0.01207 0.00588 -0.1202 0.1221 1.0000
7.000 1.2954 0.01260 0.00628 -0.1193 0.1023 1.0000
7.250 1.3186 0.01302 0.00663 -0.1186 0.0934 1.0000
7.500 1.3425 0.01336 0.00696 -0.1180 0.0876 1.0000
7.750 1.3657 0.01374 0.00731 -0.1172 0.0790 1.0000
8.250 1.4074 0.01481 0.00821 -0.1151 0.0577 1.0000
8.500 1.4294 0.01522 0.00862 -0.1142 0.0528 1.0000
8.750 1.4522 0.01555 0.00897 -0.1135 0.0503 1.0000
9.000 1.4689 0.01630 0.00961 -0.1118 0.0359 1.0000
9.250 1.4864 0.01695 0.01020 -0.1103 0.0307 1.0000
9.500 1.5046 0.01750 0.01074 -0.1088 0.0271 1.0000
9.750 1.5232 0.01791 0.01118 -0.1073 0.0251 1.0000
10.000 1.5341 0.01867 0.01192 -0.1047 0.0170 1.0000
10.250 1.5310 0.02022 0.01338 -0.1000 0.0030 1.0000
10.500 1.5427 0.02096 0.01419 -0.0976 0.0026 1.0000
10.750 1.5537 0.02177 0.01507 -0.0953 0.0024 1.0000
11.000 1.5644 0.02262 0.01599 -0.0931 0.0022 1.0000
11.250 1.5738 0.02359 0.01705 -0.0908 0.0021 1.0000
11.500 1.5833 0.02460 0.01813 -0.0887 0.0020 1.0000
11.750 1.5923 0.02570 0.01931 -0.0868 0.0020 1.0000
12.000 1.6005 0.02691 0.02060 -0.0849 0.0019 1.0000
12.250 1.6077 0.02826 0.02203 -0.0831 0.0019 1.0000
12.500 1.6137 0.02978 0.02363 -0.0813 0.0018 1.0000
12.750 1.6193 0.03140 0.02533 -0.0797 0.0017 1.0000
13.000 1.6228 0.03328 0.02732 -0.0781 0.0017 1.0000
13.250 1.6256 0.03532 0.02944 -0.0767 0.0016 1.0000
13.500 1.6261 0.03768 0.03191 -0.0754 0.0015 1.0000
13.750 1.6252 0.04028 0.03462 -0.0743 0.0015 1.0000
14.000 1.6218 0.04329 0.03775 -0.0734 0.0014 1.0000
14.250 1.6156 0.04676 0.04136 -0.0727 0.0014 1.0000
14.500 1.6014 0.05141 0.04617 -0.0724 0.0013 1.0000
14.750 1.5904 0.05598 0.05089 -0.0727 0.0013 1.0000
15.000 1.5877 0.05963 0.05465 -0.0731 0.0013 1.0000
15.250 1.5826 0.06382 0.05895 -0.0738 0.0013 1.0000
15.500 1.5774 0.06819 0.06344 -0.0748 0.0013 1.0000
15.750 1.5698 0.07310 0.06847 -0.0761 0.0013 1.0000
16.000 1.5612 0.07837 0.07387 -0.0778 0.0013 1.0000
16.250 1.5513 0.08407 0.07970 -0.0798 0.0012 1.0000
16.500 1.5394 0.09029 0.08605 -0.0822 0.0012 1.0000
16.750 1.5266 0.09687 0.09276 -0.0850 0.0012 1.0000
17.000 1.5132 0.10378 0.09981 -0.0881 0.0012 1.0000
17.250 1.4983 0.11114 0.10730 -0.0916 0.0012 1.0000
17.500 1.4839 0.11855 0.11485 -0.0953 0.0012 1.0000
17.750 1.4695 0.12614 0.12257 -0.0992 0.0012 1.0000
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