WORTMANN FX 60-126 AIRFOIL (fx60126-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 60-126 AIRFOIL (fx60126-il) Reynolds number: 200,000 Max Cl/Cd: 79.72 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60126-il-200000.txt Download as CSV file: xf-fx60126-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3581 0.09764 0.09411 -0.0439 1.0000 0.0631
-9.750 -0.4799 0.06403 0.06049 -0.0644 1.0000 0.0327
-9.500 -0.5083 0.05967 0.05615 -0.0655 1.0000 0.0325
-9.250 -0.5433 0.05769 0.05420 -0.0629 1.0000 0.0326
-9.000 -0.5766 0.05546 0.05197 -0.0615 1.0000 0.0326
-8.750 -0.5972 0.05217 0.04858 -0.0623 1.0000 0.0322
-8.500 -0.6230 0.04101 0.03616 -0.0713 0.9974 0.0277
-8.250 -0.5933 0.03637 0.03120 -0.0758 0.9938 0.0270
-8.000 -0.5629 0.03225 0.02662 -0.0798 0.9892 0.0268
-7.750 -0.5276 0.02901 0.02295 -0.0835 0.9852 0.0266
-7.500 -0.4897 0.02652 0.02007 -0.0867 0.9822 0.0269
-7.250 -0.4575 0.02476 0.01799 -0.0883 0.9770 0.0274
-7.000 -0.4234 0.02278 0.01596 -0.0904 0.9734 0.0284
-6.750 -0.3844 0.02177 0.01494 -0.0932 0.9705 0.0311
-6.500 -0.3517 0.02080 0.01384 -0.0945 0.9653 0.0332
-6.250 -0.3162 0.01927 0.01232 -0.0967 0.9606 0.0358
-6.000 -0.2743 0.01816 0.01113 -0.0998 0.9572 0.0413
-5.750 -0.2320 0.01649 0.00962 -0.1037 0.9541 0.0644
-5.500 -0.1998 0.01550 0.00878 -0.1053 0.9475 0.1073
-5.250 -0.1594 0.01461 0.00814 -0.1085 0.9438 0.1612
-5.000 -0.1163 0.01381 0.00773 -0.1123 0.9413 0.2529
-4.750 -0.0807 0.01354 0.00756 -0.1140 0.9363 0.3065
-4.500 -0.0455 0.01340 0.00743 -0.1153 0.9305 0.3406
-4.250 -0.0047 0.01325 0.00723 -0.1176 0.9267 0.3693
-4.000 0.0298 0.01317 0.00711 -0.1185 0.9205 0.3908
-3.750 0.0634 0.01312 0.00697 -0.1193 0.9137 0.4116
-3.500 0.1007 0.01301 0.00685 -0.1206 0.9095 0.4311
-3.250 0.1279 0.01303 0.00684 -0.1202 0.9004 0.4472
-3.000 0.1616 0.01292 0.00669 -0.1208 0.8950 0.4619
-2.750 0.1896 0.01290 0.00663 -0.1205 0.8864 0.4742
-2.500 0.2207 0.01276 0.00648 -0.1206 0.8796 0.4855
-2.250 0.2481 0.01272 0.00644 -0.1200 0.8698 0.4982
-2.000 0.2786 0.01260 0.00627 -0.1198 0.8624 0.5112
-1.750 0.3054 0.01258 0.00618 -0.1193 0.8514 0.5231
-1.500 0.3335 0.01248 0.00611 -0.1188 0.8426 0.5320
-1.250 0.3617 0.01239 0.00597 -0.1184 0.8330 0.5421
-1.000 0.3891 0.01236 0.00592 -0.1180 0.8224 0.5521
-0.750 0.4174 0.01226 0.00580 -0.1176 0.8129 0.5613
-0.500 0.4452 0.01219 0.00567 -0.1172 0.8012 0.5717
-0.250 0.4721 0.01212 0.00562 -0.1166 0.7887 0.5802
0.000 0.4999 0.01206 0.00551 -0.1162 0.7768 0.5894
0.250 0.5279 0.01200 0.00542 -0.1158 0.7653 0.5986
0.500 0.5555 0.01195 0.00535 -0.1155 0.7531 0.6076
0.750 0.5831 0.01194 0.00530 -0.1152 0.7397 0.6184
1.000 0.6101 0.01191 0.00530 -0.1147 0.7264 0.6278
1.250 0.6375 0.01191 0.00528 -0.1143 0.7131 0.6381
1.500 0.6650 0.01193 0.00525 -0.1140 0.6988 0.6496
1.750 0.6916 0.01191 0.00525 -0.1134 0.6831 0.6594
2.000 0.7183 0.01192 0.00523 -0.1129 0.6665 0.6700
2.250 0.7451 0.01197 0.00523 -0.1124 0.6498 0.6818
2.500 0.7715 0.01202 0.00528 -0.1119 0.6337 0.6939
2.750 0.7978 0.01208 0.00536 -0.1114 0.6190 0.7067
3.000 0.8240 0.01218 0.00546 -0.1109 0.6052 0.7208
3.250 0.8501 0.01228 0.00559 -0.1104 0.5916 0.7367
3.500 0.8759 0.01239 0.00572 -0.1098 0.5777 0.7546
3.750 0.9013 0.01249 0.00585 -0.1092 0.5631 0.7746
4.000 0.9253 0.01256 0.00597 -0.1082 0.5475 0.7969
4.250 0.9481 0.01260 0.00610 -0.1070 0.5315 0.8280
4.500 0.9657 0.01249 0.00614 -0.1045 0.5164 0.8964
4.750 0.9941 0.01262 0.00625 -0.1047 0.4990 1.0000
5.000 1.0216 0.01290 0.00647 -0.1048 0.4829 1.0000
5.250 1.0482 0.01319 0.00671 -0.1047 0.4668 1.0000
5.500 1.0741 0.01349 0.00697 -0.1044 0.4502 1.0000
5.750 1.0993 0.01379 0.00725 -0.1040 0.4321 1.0000
6.000 1.1236 0.01413 0.00753 -0.1034 0.4130 1.0000
6.250 1.1473 0.01453 0.00785 -0.1027 0.3936 1.0000
6.500 1.1709 0.01489 0.00821 -0.1020 0.3722 1.0000
6.750 1.1934 0.01534 0.00859 -0.1012 0.3510 1.0000
7.000 1.2151 0.01585 0.00903 -0.1003 0.3285 1.0000
7.250 1.2360 0.01639 0.00951 -0.0993 0.3039 1.0000
7.500 1.2557 0.01702 0.01006 -0.0981 0.2791 1.0000
7.750 1.2740 0.01774 0.01067 -0.0968 0.2520 1.0000
8.000 1.2903 0.01859 0.01135 -0.0952 0.2265 1.0000
8.250 1.3074 0.01939 0.01209 -0.0937 0.2025 1.0000
8.500 1.3224 0.02031 0.01289 -0.0920 0.1838 1.0000
8.750 1.3367 0.02127 0.01377 -0.0902 0.1683 1.0000
9.000 1.3510 0.02217 0.01465 -0.0884 0.1545 1.0000
9.250 1.3630 0.02308 0.01554 -0.0862 0.1428 1.0000
9.500 1.3733 0.02411 0.01656 -0.0839 0.1328 1.0000
9.750 1.3800 0.02546 0.01781 -0.0813 0.1242 1.0000
10.000 1.3929 0.02637 0.01884 -0.0795 0.1159 1.0000
10.250 1.4008 0.02772 0.02016 -0.0773 0.1096 1.0000
10.500 1.4124 0.02878 0.02131 -0.0755 0.1035 1.0000
10.750 1.4191 0.03037 0.02282 -0.0735 0.0984 1.0000
11.000 1.4302 0.03159 0.02418 -0.0719 0.0937 1.0000
11.250 1.4388 0.03304 0.02568 -0.0702 0.0893 1.0000
11.500 1.4478 0.03489 0.02748 -0.0687 0.0850 1.0000
11.750 1.4573 0.03629 0.02908 -0.0672 0.0814 1.0000
12.000 1.4662 0.03785 0.03072 -0.0659 0.0781 1.0000
12.250 1.4752 0.03959 0.03246 -0.0646 0.0753 1.0000
12.500 1.4876 0.04146 0.03438 -0.0635 0.0727 1.0000
12.750 1.4965 0.04320 0.03630 -0.0624 0.0707 1.0000
13.000 1.5052 0.04500 0.03826 -0.0613 0.0686 1.0000
13.250 1.5131 0.04683 0.04017 -0.0604 0.0666 1.0000
13.500 1.5213 0.04869 0.04205 -0.0596 0.0646 1.0000
13.750 1.5298 0.05100 0.04443 -0.0588 0.0623 1.0000
14.000 1.5299 0.05342 0.04708 -0.0581 0.0607 1.0000
14.250 1.5297 0.05598 0.04982 -0.0576 0.0587 1.0000
14.500 1.5305 0.05852 0.05246 -0.0574 0.0568 1.0000
14.750 1.5326 0.06104 0.05501 -0.0573 0.0549 1.0000
15.000 1.5385 0.06399 0.05799 -0.0569 0.0524 1.0000
15.250 1.5326 0.06743 0.06169 -0.0573 0.0515 1.0000
15.500 1.5273 0.07109 0.06557 -0.0579 0.0502 1.0000
15.750 1.5217 0.07502 0.06970 -0.0588 0.0489 1.0000
16.000 1.5170 0.07898 0.07383 -0.0599 0.0475 1.0000
16.250 1.5138 0.08284 0.07780 -0.0612 0.0461 1.0000
16.500 1.5131 0.08635 0.08136 -0.0624 0.0447 1.0000
16.750 1.5125 0.09012 0.08514 -0.0630 0.0428 1.0000
17.000 1.5011 0.09566 0.09094 -0.0656 0.0422 1.0000
17.250 1.4890 0.10156 0.09709 -0.0686 0.0412 1.0000
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