FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 100,000 Max Cl/Cd: 48.81 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60160-il-100000-n5.txt Download as CSV file: xf-fx60160-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-160 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4457 0.09044 0.08548 -0.0653 1.0000 0.0379
-11.000 -0.4761 0.08275 0.07783 -0.0683 1.0000 0.0375
-10.750 -0.5098 0.07693 0.07202 -0.0697 1.0000 0.0373
-10.500 -0.5370 0.06968 0.06464 -0.0754 0.9953 0.0370
-10.250 -0.5566 0.06262 0.05730 -0.0827 0.9853 0.0371
-10.000 -0.5723 0.05741 0.05176 -0.0873 0.9731 0.0374
-9.750 -0.5781 0.05244 0.04635 -0.0900 0.9611 0.0380
-9.500 -0.5838 0.04806 0.04129 -0.0911 0.9489 0.0395
-9.250 -0.5591 0.04582 0.03905 -0.0935 0.9449 0.0413
-9.000 -0.5454 0.04416 0.03726 -0.0933 0.9353 0.0427
-8.750 -0.5230 0.04173 0.03450 -0.0952 0.9305 0.0450
-8.500 -0.5114 0.03966 0.03200 -0.0943 0.9204 0.0472
-8.250 -0.4867 0.03730 0.02905 -0.0956 0.9158 0.0490
-8.000 -0.4704 0.03529 0.02687 -0.0949 0.9072 0.0506
-7.750 -0.4423 0.03370 0.02517 -0.0962 0.9029 0.0527
-7.500 -0.4145 0.03213 0.02339 -0.0970 0.8982 0.0543
-7.250 -0.3917 0.03079 0.02184 -0.0966 0.8910 0.0555
-7.000 -0.3603 0.02943 0.02026 -0.0977 0.8874 0.0574
-6.750 -0.3354 0.02848 0.01911 -0.0975 0.8812 0.0596
-6.500 -0.3075 0.02755 0.01798 -0.0978 0.8758 0.0611
-6.250 -0.2758 0.02613 0.01656 -0.0987 0.8726 0.0627
-6.000 -0.2524 0.02526 0.01571 -0.0982 0.8663 0.0643
-5.750 -0.2258 0.02446 0.01490 -0.0982 0.8612 0.0662
-5.500 -0.1951 0.02367 0.01408 -0.0991 0.8577 0.0693
-5.250 -0.1738 0.02318 0.01351 -0.0982 0.8508 0.0725
-5.000 -0.1477 0.02251 0.01279 -0.0982 0.8458 0.0753
-4.750 -0.1183 0.02172 0.01198 -0.0990 0.8424 0.0790
-4.500 -0.0991 0.02132 0.01153 -0.0979 0.8350 0.0829
-4.250 -0.0711 0.02080 0.01090 -0.0983 0.8304 0.0888
-4.000 -0.0400 0.02012 0.01024 -0.0994 0.8271 0.1023
-3.750 -0.0221 0.01965 0.00992 -0.0982 0.8198 0.1282
-3.500 -0.0034 0.01784 0.00919 -0.0983 0.8148 0.3533
-3.250 0.0223 0.01749 0.00955 -0.0976 0.8114 0.5139
-3.000 0.0410 0.01788 0.01001 -0.0955 0.8042 0.5651
-2.750 0.0697 0.01824 0.01030 -0.0950 0.7998 0.5999
-2.500 0.1020 0.01856 0.01051 -0.0953 0.7965 0.6270
-2.250 0.1205 0.01903 0.01095 -0.0931 0.7894 0.6437
-2.000 0.1472 0.01938 0.01123 -0.0922 0.7847 0.6602
-1.750 0.1786 0.01952 0.01126 -0.0925 0.7812 0.6736
-1.500 0.1985 0.01969 0.01138 -0.0910 0.7745 0.6809
-1.250 0.2268 0.01964 0.01121 -0.0913 0.7694 0.6873
-1.000 0.2586 0.01958 0.01106 -0.0919 0.7658 0.6923
-0.750 0.2799 0.01968 0.01109 -0.0911 0.7590 0.7001
-0.500 0.3060 0.01972 0.01109 -0.0906 0.7538 0.7056
-0.250 0.3380 0.01966 0.01094 -0.0913 0.7499 0.7130
0.000 0.3575 0.01979 0.01107 -0.0899 0.7429 0.7190
0.250 0.3845 0.01978 0.01102 -0.0898 0.7377 0.7236
0.500 0.4178 0.01967 0.01082 -0.0910 0.7339 0.7291
0.750 0.4361 0.01982 0.01098 -0.0895 0.7264 0.7337
1.000 0.4640 0.01979 0.01093 -0.0895 0.7213 0.7376
1.250 0.4947 0.01973 0.01083 -0.0902 0.7170 0.7423
1.500 0.5145 0.01990 0.01100 -0.0891 0.7095 0.7474
1.750 0.5436 0.01983 0.01094 -0.0893 0.7047 0.7508
2.000 0.5674 0.01991 0.01103 -0.0887 0.6987 0.7550
2.250 0.5916 0.01999 0.01112 -0.0883 0.6921 0.7598
2.500 0.6240 0.01991 0.01103 -0.0892 0.6877 0.7637
2.750 0.6415 0.02010 0.01130 -0.0876 0.6801 0.7675
3.000 0.6694 0.02010 0.01131 -0.0876 0.6745 0.7717
3.250 0.6954 0.02018 0.01142 -0.0875 0.6685 0.7763
3.500 0.7171 0.02030 0.01161 -0.0866 0.6613 0.7801
3.750 0.7489 0.02021 0.01154 -0.0873 0.6567 0.7839
4.000 0.7648 0.02048 0.01192 -0.0855 0.6482 0.7885
4.250 0.7953 0.02047 0.01193 -0.0861 0.6426 0.7929
4.500 0.8139 0.02066 0.01223 -0.0846 0.6350 0.7967
4.750 0.8406 0.02070 0.01233 -0.0844 0.6285 0.8010
5.000 0.8634 0.02087 0.01259 -0.0838 0.6211 0.8056
5.250 0.8888 0.02088 0.01267 -0.0834 0.6131 0.8099
5.500 0.9077 0.02096 0.01285 -0.0818 0.6025 0.8144
5.750 0.9317 0.02087 0.01282 -0.0810 0.5912 0.8193
6.000 0.9532 0.02077 0.01276 -0.0797 0.5774 0.8241
6.250 0.9706 0.02073 0.01278 -0.0777 0.5618 0.8291
6.500 0.9864 0.02077 0.01286 -0.0755 0.5446 0.8350
6.750 1.0008 0.02084 0.01299 -0.0731 0.5273 0.8407
7.000 1.0153 0.02096 0.01314 -0.0707 0.5093 0.8471
7.250 1.0308 0.02112 0.01331 -0.0686 0.4893 0.8541
7.500 1.0409 0.02148 0.01369 -0.0657 0.4655 0.8624
7.750 1.0515 0.02189 0.01407 -0.0630 0.4383 0.8721
8.000 1.0613 0.02244 0.01461 -0.0604 0.4091 0.8849
8.250 1.0687 0.02324 0.01535 -0.0579 0.3694 0.9084
8.500 1.0657 0.02441 0.01628 -0.0541 0.3177 1.0000
8.750 1.0544 0.02653 0.01790 -0.0501 0.2403 1.0000
9.000 1.0389 0.02931 0.02010 -0.0463 0.1642 1.0000
9.250 1.0302 0.03196 0.02233 -0.0436 0.1124 1.0000
9.500 1.0301 0.03410 0.02430 -0.0417 0.0964 1.0000
9.750 1.0342 0.03598 0.02617 -0.0403 0.0890 1.0000
10.000 1.0384 0.03789 0.02813 -0.0390 0.0841 1.0000
10.250 1.0403 0.04003 0.03029 -0.0377 0.0805 1.0000
10.500 1.0458 0.04192 0.03226 -0.0367 0.0779 1.0000
10.750 1.0517 0.04380 0.03425 -0.0357 0.0754 1.0000
11.000 1.0574 0.04573 0.03627 -0.0348 0.0733 1.0000
11.250 1.0632 0.04768 0.03829 -0.0339 0.0714 1.0000
11.500 1.0697 0.04958 0.04023 -0.0331 0.0697 1.0000
11.750 1.0772 0.05140 0.04205 -0.0322 0.0680 1.0000
12.000 1.0890 0.05285 0.04351 -0.0313 0.0663 1.0000
12.250 1.1030 0.05417 0.04494 -0.0307 0.0648 1.0000
12.500 1.1178 0.05546 0.04632 -0.0301 0.0630 1.0000
12.750 1.1336 0.05671 0.04764 -0.0295 0.0613 1.0000
13.000 1.1514 0.05785 0.04884 -0.0289 0.0599 1.0000
13.250 1.1706 0.05896 0.05002 -0.0284 0.0587 1.0000
13.500 1.1913 0.06005 0.05115 -0.0279 0.0575 1.0000
13.750 1.2156 0.06107 0.05218 -0.0275 0.0562 1.0000
14.000 1.2443 0.06221 0.05333 -0.0273 0.0547 1.0000
14.250 1.2538 0.06419 0.05555 -0.0267 0.0537 1.0000
14.500 1.2641 0.06627 0.05786 -0.0263 0.0525 1.0000
14.750 1.2750 0.06847 0.06031 -0.0259 0.0514 1.0000
15.000 1.2820 0.07089 0.06294 -0.0255 0.0502 1.0000
15.250 1.2849 0.07349 0.06574 -0.0252 0.0488 1.0000
15.500 1.2867 0.07612 0.06851 -0.0251 0.0474 1.0000
15.750 1.2914 0.07853 0.07097 -0.0251 0.0459 1.0000
16.000 1.2995 0.08116 0.07363 -0.0252 0.0444 1.0000
16.250 1.2869 0.08524 0.07805 -0.0255 0.0435 1.0000
16.500 1.2746 0.08960 0.08273 -0.0261 0.0425 1.0000
16.750 1.2626 0.09422 0.08763 -0.0271 0.0415 1.0000
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