WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126/1 AIRFOIL (fx601261-il) Reynolds number: 50,000 Max Cl/Cd: 39.41 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx601261-il-50000-n5.txt Download as CSV file: xf-fx601261-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3255 0.10505 0.09793 -0.0442 1.0000 0.0363
-9.500 -0.3276 0.10108 0.09405 -0.0452 1.0000 0.0356
-9.250 -0.3316 0.09685 0.08993 -0.0465 1.0000 0.0347
-8.750 -0.3580 0.08461 0.07796 -0.0514 1.0000 0.0324
-8.500 -0.3667 0.08086 0.07432 -0.0518 1.0000 0.0322
-8.250 -0.3794 0.07731 0.07090 -0.0519 1.0000 0.0319
-8.000 -0.3986 0.07406 0.06778 -0.0513 1.0000 0.0316
-7.750 -0.4218 0.07107 0.06491 -0.0504 1.0000 0.0313
-7.500 -0.4432 0.06730 0.06118 -0.0515 1.0000 0.0310
-7.250 -0.4610 0.06306 0.05690 -0.0541 1.0000 0.0307
-7.000 -0.4721 0.05885 0.05253 -0.0565 1.0000 0.0303
-6.750 -0.4748 0.05460 0.04803 -0.0590 1.0000 0.0300
-6.500 -0.4525 0.04914 0.04204 -0.0657 0.9947 0.0297
-6.250 -0.4209 0.04457 0.03689 -0.0714 0.9878 0.0296
-6.000 -0.3876 0.04105 0.03282 -0.0755 0.9815 0.0296
-5.750 -0.3536 0.03834 0.02967 -0.0785 0.9750 0.0298
-5.500 -0.3207 0.03623 0.02720 -0.0805 0.9685 0.0301
-5.250 -0.2873 0.03453 0.02520 -0.0822 0.9620 0.0309
-5.000 -0.2549 0.03320 0.02359 -0.0836 0.9552 0.0321
-4.750 -0.2212 0.03187 0.02211 -0.0856 0.9483 0.0342
-4.500 -0.1870 0.03073 0.02078 -0.0877 0.9415 0.0368
-4.250 -0.1510 0.02968 0.01945 -0.0899 0.9342 0.0398
-4.000 -0.1124 0.02840 0.01807 -0.0931 0.9276 0.0439
-3.750 -0.0753 0.02727 0.01682 -0.0958 0.9200 0.0508
-3.500 -0.0283 0.02512 0.01526 -0.1014 0.9154 0.1504
-3.250 0.0034 0.02459 0.01574 -0.1032 0.9064 0.3545
-3.000 0.0409 0.02525 0.01644 -0.1042 0.9002 0.4364
-2.750 0.0643 0.02605 0.01728 -0.1024 0.8900 0.4832
-2.500 0.1037 0.02611 0.01711 -0.1040 0.8846 0.5089
-2.250 0.1307 0.02614 0.01698 -0.1038 0.8746 0.5249
-2.000 0.1707 0.02598 0.01659 -0.1056 0.8689 0.5415
-1.750 0.1980 0.02598 0.01643 -0.1056 0.8583 0.5561
-1.500 0.2345 0.02584 0.01612 -0.1068 0.8513 0.5720
-1.250 0.2640 0.02582 0.01595 -0.1071 0.8413 0.5861
-1.000 0.2957 0.02575 0.01576 -0.1076 0.8328 0.5989
-0.750 0.3277 0.02567 0.01558 -0.1082 0.8243 0.6114
-0.500 0.3561 0.02569 0.01552 -0.1083 0.8148 0.6245
-0.250 0.3903 0.02557 0.01531 -0.1091 0.8072 0.6386
0.000 0.4164 0.02564 0.01532 -0.1088 0.7963 0.6521
0.250 0.4522 0.02543 0.01505 -0.1097 0.7891 0.6666
0.500 0.4776 0.02551 0.01510 -0.1093 0.7774 0.6801
0.750 0.5042 0.02554 0.01512 -0.1089 0.7670 0.6940
1.000 0.5369 0.02536 0.01494 -0.1092 0.7591 0.7093
1.250 0.5596 0.02551 0.01512 -0.1083 0.7475 0.7251
1.500 0.5863 0.02551 0.01516 -0.1078 0.7380 0.7431
1.750 0.6141 0.02537 0.01508 -0.1072 0.7288 0.7628
2.000 0.6358 0.02541 0.01522 -0.1059 0.7169 0.7852
2.250 0.6593 0.02529 0.01520 -0.1046 0.7063 0.8127
2.500 0.6851 0.02497 0.01498 -0.1034 0.6970 0.8525
2.750 0.7095 0.02491 0.01505 -0.1027 0.6846 1.0000
3.000 0.7423 0.02518 0.01527 -0.1040 0.6736 1.0000
3.250 0.7801 0.02515 0.01515 -0.1056 0.6651 1.0000
3.500 0.8072 0.02552 0.01549 -0.1057 0.6521 1.0000
3.750 0.8351 0.02580 0.01576 -0.1057 0.6392 1.0000
4.000 0.8637 0.02600 0.01594 -0.1057 0.6268 1.0000
4.250 0.8939 0.02613 0.01604 -0.1058 0.6151 1.0000
4.500 0.9243 0.02623 0.01616 -0.1059 0.6035 1.0000
4.750 0.9494 0.02659 0.01655 -0.1053 0.5896 1.0000
5.000 0.9749 0.02688 0.01687 -0.1048 0.5754 1.0000
5.250 1.0006 0.02712 0.01715 -0.1041 0.5606 1.0000
5.500 1.0260 0.02735 0.01741 -0.1034 0.5452 1.0000
5.750 1.0507 0.02763 0.01773 -0.1026 0.5296 1.0000
6.000 1.0747 0.02791 0.01804 -0.1016 0.5130 1.0000
6.250 1.0985 0.02817 0.01831 -0.1006 0.4958 1.0000
6.500 1.1216 0.02846 0.01861 -0.0995 0.4781 1.0000
6.750 1.1405 0.02899 0.01922 -0.0980 0.4592 1.0000
7.000 1.1593 0.02955 0.01984 -0.0966 0.4402 1.0000
7.250 1.1783 0.03006 0.02038 -0.0951 0.4210 1.0000
7.500 1.1972 0.03058 0.02091 -0.0936 0.4017 1.0000
7.750 1.2125 0.03134 0.02173 -0.0918 0.3817 1.0000
8.000 1.2269 0.03215 0.02258 -0.0899 0.3616 1.0000
8.250 1.2412 0.03298 0.02342 -0.0880 0.3421 1.0000
8.500 1.2536 0.03393 0.02436 -0.0860 0.3228 1.0000
8.750 1.2621 0.03505 0.02553 -0.0837 0.3035 1.0000
9.000 1.2705 0.03623 0.02671 -0.0814 0.2855 1.0000
9.250 1.2777 0.03757 0.02804 -0.0792 0.2679 1.0000
9.500 1.2842 0.03903 0.02953 -0.0771 0.2516 1.0000
9.750 1.2905 0.04059 0.03109 -0.0751 0.2370 1.0000
10.000 1.2970 0.04228 0.03281 -0.0734 0.2235 1.0000
10.250 1.3028 0.04409 0.03465 -0.0718 0.2108 1.0000
10.500 1.3087 0.04597 0.03656 -0.0703 0.1995 1.0000
10.750 1.3150 0.04787 0.03848 -0.0690 0.1894 1.0000
11.000 1.3203 0.05001 0.04077 -0.0678 0.1794 1.0000
11.250 1.3255 0.05213 0.04292 -0.0667 0.1705 1.0000
11.500 1.3287 0.05450 0.04539 -0.0657 0.1616 1.0000
11.750 1.3311 0.05705 0.04809 -0.0649 0.1535 1.0000
12.000 1.3340 0.05949 0.05057 -0.0641 0.1462 1.0000
12.250 1.3354 0.06237 0.05365 -0.0636 0.1395 1.0000
12.500 1.3399 0.06489 0.05624 -0.0631 0.1336 1.0000
12.750 1.3457 0.06754 0.05905 -0.0626 0.1286 1.0000
13.000 1.3462 0.07092 0.06271 -0.0625 0.1238 1.0000
13.250 1.3520 0.07360 0.06550 -0.0621 0.1194 1.0000
13.500 1.3577 0.07648 0.06849 -0.0618 0.1155 1.0000
13.750 1.3485 0.08135 0.07372 -0.0626 0.1123 1.0000
14.000 1.3410 0.08609 0.07873 -0.0634 0.1094 1.0000
14.250 1.3386 0.09016 0.08296 -0.0641 0.1066 1.0000
14.500 1.3486 0.09251 0.08533 -0.0639 0.1037 1.0000
14.750 1.3216 0.10054 0.09372 -0.0671 0.1024 1.0000
15.000 1.2866 0.11069 0.10418 -0.0723 0.1015 1.0000
15.250 1.2314 0.12633 0.12009 -0.0816 0.1011 1.0000
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