WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 100,000 Max Cl/Cd: 57.63 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60126-il-100000.txt Download as CSV file: xf-fx60126-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3346 0.10237 0.09745 -0.0383 1.0000 0.1304
-9.250 -0.3857 0.10079 0.09613 -0.0445 1.0000 0.1366
-9.000 -0.4446 0.07572 0.07117 -0.0568 1.0000 0.0717
-8.750 -0.4211 0.07600 0.07147 -0.0516 1.0000 0.0685
-8.500 -0.5413 0.06296 0.05833 -0.0619 1.0000 0.0595
-8.250 -0.5465 0.05963 0.05503 -0.0608 1.0000 0.0586
-8.000 -0.5579 0.05559 0.05086 -0.0616 1.0000 0.0581
-7.750 -0.5624 0.05131 0.04640 -0.0627 1.0000 0.0567
-7.500 -0.5618 0.04628 0.04099 -0.0649 1.0000 0.0553
-7.250 -0.5524 0.04102 0.03515 -0.0674 1.0000 0.0539
-7.000 -0.5343 0.03625 0.02961 -0.0697 1.0000 0.0525
-6.750 -0.5126 0.03315 0.02602 -0.0706 1.0000 0.0526
-6.500 -0.4898 0.03087 0.02344 -0.0710 1.0000 0.0535
-6.250 -0.4661 0.02895 0.02126 -0.0711 1.0000 0.0552
-6.000 -0.4418 0.02727 0.01930 -0.0710 1.0000 0.0578
-5.750 -0.4182 0.02566 0.01758 -0.0709 1.0000 0.0618
-5.500 -0.3945 0.02465 0.01647 -0.0709 1.0000 0.0701
-5.250 -0.3703 0.02321 0.01514 -0.0709 1.0000 0.0816
-5.000 -0.3402 0.02167 0.01385 -0.0725 0.9991 0.1136
-4.750 -0.2935 0.02052 0.01299 -0.0775 0.9938 0.1811
-4.500 -0.2501 0.01971 0.01265 -0.0817 0.9872 0.2718
-4.250 -0.2075 0.01993 0.01307 -0.0848 0.9803 0.3435
-4.000 -0.1672 0.02049 0.01360 -0.0872 0.9721 0.3886
-3.750 -0.1303 0.02103 0.01412 -0.0888 0.9633 0.4212
-3.500 -0.0879 0.02163 0.01470 -0.0912 0.9557 0.4512
-3.250 -0.0532 0.02192 0.01486 -0.0925 0.9453 0.4754
-3.000 -0.0137 0.02223 0.01519 -0.0942 0.9372 0.4951
-2.750 0.0222 0.02247 0.01542 -0.0953 0.9275 0.5143
-2.500 0.0563 0.02265 0.01557 -0.0962 0.9180 0.5324
-2.250 0.0980 0.02271 0.01558 -0.0984 0.9107 0.5510
-2.000 0.1293 0.02276 0.01560 -0.0989 0.9004 0.5654
-1.750 0.1748 0.02264 0.01543 -0.1017 0.8945 0.5815
-1.500 0.2058 0.02259 0.01536 -0.1021 0.8834 0.5947
-1.250 0.2562 0.02223 0.01494 -0.1056 0.8784 0.6092
-1.000 0.2864 0.02211 0.01480 -0.1058 0.8667 0.6222
-0.750 0.3272 0.02179 0.01445 -0.1076 0.8597 0.6367
-0.500 0.3611 0.02157 0.01420 -0.1084 0.8497 0.6497
-0.250 0.3916 0.02139 0.01404 -0.1084 0.8396 0.6601
0.000 0.4294 0.02100 0.01365 -0.1095 0.8324 0.6723
0.250 0.4581 0.02084 0.01349 -0.1093 0.8206 0.6845
0.500 0.4932 0.02044 0.01308 -0.1098 0.8119 0.6981
0.750 0.5245 0.02011 0.01276 -0.1097 0.8012 0.7117
1.000 0.5506 0.01993 0.01263 -0.1088 0.7890 0.7239
1.250 0.5803 0.01966 0.01238 -0.1084 0.7787 0.7370
1.500 0.6113 0.01932 0.01206 -0.1082 0.7691 0.7508
1.750 0.6371 0.01922 0.01199 -0.1075 0.7565 0.7649
2.000 0.6639 0.01901 0.01183 -0.1067 0.7444 0.7807
2.250 0.6923 0.01869 0.01152 -0.1059 0.7331 0.7982
2.500 0.7205 0.01835 0.01119 -0.1051 0.7217 0.8181
2.750 0.7432 0.01821 0.01114 -0.1036 0.7082 0.8403
3.000 0.7648 0.01803 0.01105 -0.1018 0.6953 0.8685
3.250 0.7854 0.01769 0.01082 -0.0997 0.6824 0.9126
3.500 0.8245 0.01747 0.01060 -0.1018 0.6668 1.0000
3.750 0.8610 0.01750 0.01051 -0.1036 0.6503 1.0000
4.000 0.8941 0.01757 0.01047 -0.1045 0.6336 1.0000
4.250 0.9249 0.01771 0.01053 -0.1049 0.6175 1.0000
4.500 0.9542 0.01788 0.01062 -0.1050 0.6010 1.0000
4.750 0.9825 0.01806 0.01072 -0.1048 0.5840 1.0000
5.000 1.0101 0.01829 0.01088 -0.1045 0.5672 1.0000
5.250 1.0372 0.01856 0.01109 -0.1042 0.5506 1.0000
5.500 1.0636 0.01885 0.01131 -0.1037 0.5331 1.0000
5.750 1.0876 0.01917 0.01167 -0.1029 0.5136 1.0000
6.000 1.1118 0.01947 0.01195 -0.1020 0.4938 1.0000
6.250 1.1361 0.01977 0.01220 -0.1012 0.4742 1.0000
6.500 1.1595 0.02012 0.01251 -0.1003 0.4536 1.0000
6.750 1.1810 0.02050 0.01292 -0.0991 0.4309 1.0000
7.000 1.2032 0.02091 0.01324 -0.0980 0.4093 1.0000
7.250 1.2228 0.02143 0.01378 -0.0966 0.3844 1.0000
7.500 1.2418 0.02199 0.01427 -0.0951 0.3589 1.0000
7.750 1.2592 0.02268 0.01484 -0.0934 0.3323 1.0000
8.000 1.2752 0.02349 0.01559 -0.0917 0.3049 1.0000
8.250 1.2909 0.02447 0.01645 -0.0899 0.2796 1.0000
8.500 1.3061 0.02555 0.01737 -0.0882 0.2565 1.0000
8.750 1.3205 0.02667 0.01845 -0.0863 0.2350 1.0000
9.000 1.3343 0.02787 0.01955 -0.0846 0.2157 1.0000
9.250 1.3477 0.02910 0.02069 -0.0827 0.1988 1.0000
9.500 1.3613 0.03039 0.02190 -0.0810 0.1840 1.0000
9.750 1.3756 0.03181 0.02330 -0.0794 0.1705 1.0000
10.000 1.3900 0.03330 0.02483 -0.0779 0.1587 1.0000
10.250 1.4062 0.03484 0.02632 -0.0766 0.1489 1.0000
10.500 1.4235 0.03630 0.02774 -0.0755 0.1403 1.0000
10.750 1.4378 0.03802 0.02961 -0.0740 0.1326 1.0000
11.000 1.4662 0.04007 0.03144 -0.0747 0.1243 1.0000
11.250 1.4711 0.04167 0.03344 -0.0719 0.1194 1.0000
11.500 1.4885 0.04347 0.03530 -0.0709 0.1141 1.0000
11.750 1.5131 0.04601 0.03789 -0.0711 0.1093 1.0000
12.000 1.5175 0.04806 0.04027 -0.0686 0.1060 1.0000
12.250 1.5249 0.05005 0.04245 -0.0667 0.1027 1.0000
12.500 1.5577 0.05287 0.04513 -0.0681 0.0982 1.0000
12.750 1.5482 0.05524 0.04793 -0.0644 0.0969 1.0000
13.000 1.5392 0.05811 0.05117 -0.0614 0.0956 1.0000
13.250 1.5288 0.06134 0.05474 -0.0589 0.0944 1.0000
13.500 1.5162 0.06492 0.05864 -0.0568 0.0934 1.0000
13.750 1.5007 0.06892 0.06295 -0.0552 0.0926 1.0000
14.000 1.4814 0.07343 0.06776 -0.0542 0.0920 1.0000
14.250 1.4568 0.07874 0.07337 -0.0540 0.0916 1.0000
14.500 1.4231 0.08543 0.08037 -0.0550 0.0918 1.0000
14.750 1.3773 0.09443 0.08970 -0.0582 0.0927 1.0000
15.000 1.3162 0.10714 0.10269 -0.0650 0.0943 1.0000
15.250 1.2390 0.12592 0.12167 -0.0771 0.0966 1.0000
15.500 1.1796 0.14588 0.14168 -0.0895 0.0985 1.0000
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