FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 200,000 Max Cl/Cd: 72.33 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60160-il-200000.txt Download as CSV file: xf-fx60160-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2808 0.09113 0.08793 -0.0664 0.9848 0.0817
-10.250 -0.2778 0.08530 0.08210 -0.0709 0.9827 0.0857
-10.000 -0.3331 0.07070 0.06750 -0.0839 0.9764 0.0889
-9.750 -0.5241 0.07294 0.06907 -0.0902 0.9706 0.0764
-9.500 -0.4953 0.06550 0.06194 -0.0906 0.9716 0.0792
-9.250 -0.4739 0.06251 0.05893 -0.0932 0.9667 0.0818
-9.000 -0.4725 0.05811 0.05423 -0.0987 0.9563 0.0874
-8.750 -0.4827 0.05321 0.04893 -0.1012 0.9439 0.0923
-8.500 -0.4499 0.05045 0.04626 -0.1037 0.9419 0.0967
-8.250 -0.4627 0.03939 0.03367 -0.1025 0.9288 0.0622
-8.000 -0.4343 0.03556 0.02946 -0.1048 0.9261 0.0615
-7.750 -0.4162 0.03304 0.02662 -0.1042 0.9183 0.0613
-7.500 -0.3868 0.03030 0.02355 -0.1055 0.9142 0.0607
-7.250 -0.3520 0.02818 0.02111 -0.1075 0.9117 0.0614
-7.000 -0.3153 0.02680 0.01941 -0.1095 0.9097 0.0631
-6.750 -0.2967 0.02590 0.01832 -0.1080 0.9006 0.0636
-6.500 -0.2628 0.02378 0.01605 -0.1094 0.8976 0.0646
-6.250 -0.2271 0.02199 0.01427 -0.1112 0.8954 0.0671
-6.000 -0.2042 0.02124 0.01351 -0.1105 0.8885 0.0694
-5.750 -0.1740 0.02034 0.01256 -0.1110 0.8838 0.0715
-5.500 -0.1403 0.01942 0.01159 -0.1122 0.8807 0.0740
-5.250 -0.1150 0.01891 0.01100 -0.1118 0.8746 0.0763
-5.000 -0.0921 0.01788 0.01004 -0.1113 0.8688 0.0803
-4.750 -0.0615 0.01713 0.00930 -0.1121 0.8651 0.0849
-4.500 -0.0392 0.01671 0.00882 -0.1114 0.8585 0.0890
-4.250 -0.0147 0.01603 0.00817 -0.1112 0.8528 0.0962
-4.000 0.0161 0.01541 0.00753 -0.1122 0.8491 0.1094
-3.750 0.0359 0.01487 0.00715 -0.1112 0.8421 0.1436
-3.500 0.0469 0.01291 0.00686 -0.1096 0.8362 0.5190
-3.250 0.0786 0.01317 0.00721 -0.1096 0.8328 0.5877
-3.000 0.1000 0.01361 0.00762 -0.1080 0.8257 0.6127
-2.750 0.1287 0.01404 0.00801 -0.1075 0.8208 0.6326
-2.500 0.1611 0.01436 0.00825 -0.1078 0.8172 0.6472
-2.250 0.1825 0.01475 0.00861 -0.1063 0.8103 0.6598
-2.000 0.2101 0.01506 0.00888 -0.1057 0.8052 0.6717
-1.750 0.2411 0.01533 0.00911 -0.1056 0.8013 0.6809
-1.500 0.2618 0.01564 0.00942 -0.1040 0.7945 0.6920
-1.250 0.2881 0.01587 0.00963 -0.1032 0.7892 0.7011
-1.000 0.3193 0.01589 0.00957 -0.1036 0.7853 0.7088
-0.750 0.3401 0.01602 0.00972 -0.1023 0.7785 0.7139
-0.500 0.3689 0.01597 0.00957 -0.1028 0.7731 0.7211
-0.250 0.3998 0.01592 0.00945 -0.1032 0.7692 0.7247
0.000 0.4204 0.01601 0.00958 -0.1019 0.7623 0.7292
0.250 0.4490 0.01601 0.00950 -0.1023 0.7570 0.7368
0.500 0.4788 0.01599 0.00946 -0.1023 0.7530 0.7418
0.750 0.4986 0.01612 0.00964 -0.1009 0.7459 0.7484
1.000 0.5268 0.01608 0.00955 -0.1011 0.7406 0.7542
1.250 0.5579 0.01602 0.00945 -0.1016 0.7365 0.7579
1.500 0.5777 0.01610 0.00959 -0.1003 0.7291 0.7626
1.750 0.6078 0.01606 0.00949 -0.1010 0.7239 0.7677
2.000 0.6355 0.01602 0.00946 -0.1010 0.7188 0.7710
2.250 0.6574 0.01606 0.00956 -0.1000 0.7118 0.7751
2.500 0.6878 0.01601 0.00947 -0.1006 0.7068 0.7795
2.750 0.7135 0.01608 0.00955 -0.1005 0.7003 0.7839
3.000 0.7380 0.01603 0.00955 -0.0999 0.6938 0.7874
3.250 0.7698 0.01597 0.00946 -0.1006 0.6892 0.7913
3.500 0.7901 0.01608 0.00967 -0.0994 0.6813 0.7956
3.750 0.8201 0.01604 0.00961 -0.1000 0.6754 0.7996
4.000 0.8432 0.01602 0.00966 -0.0991 0.6677 0.8033
4.250 0.8710 0.01584 0.00948 -0.0990 0.6593 0.8073
4.500 0.8937 0.01576 0.00945 -0.0980 0.6490 0.8115
4.750 0.9220 0.01556 0.00922 -0.0980 0.6392 0.8155
5.000 0.9444 0.01535 0.00905 -0.0967 0.6276 0.8194
5.250 0.9649 0.01525 0.00901 -0.0953 0.6155 0.8237
5.500 0.9882 0.01519 0.00897 -0.0944 0.6041 0.8280
5.750 1.0102 0.01506 0.00886 -0.0932 0.5913 0.8320
6.000 1.0316 0.01498 0.00881 -0.0919 0.5784 0.8365
6.250 1.0503 0.01496 0.00881 -0.0901 0.5631 0.8413
6.500 1.0663 0.01498 0.00886 -0.0879 0.5446 0.8460
6.750 1.0803 0.01500 0.00893 -0.0852 0.5248 0.8509
7.000 1.0937 0.01512 0.00902 -0.0825 0.5034 0.8567
7.250 1.1019 0.01530 0.00916 -0.0788 0.4773 0.8623
7.500 1.1060 0.01558 0.00938 -0.0744 0.4480 0.8689
7.750 1.1050 0.01620 0.00981 -0.0694 0.4072 0.8769
8.000 1.0965 0.01718 0.01052 -0.0635 0.3480 0.8866
8.250 1.0788 0.01887 0.01175 -0.0571 0.2612 0.8996
8.500 1.0585 0.02171 0.01398 -0.0521 0.1503 0.9304
8.750 1.0497 0.02379 0.01575 -0.0484 0.1087 1.0000
9.000 1.0511 0.02559 0.01745 -0.0462 0.0970 1.0000
9.250 1.0580 0.02709 0.01900 -0.0447 0.0912 1.0000
9.500 1.0614 0.02887 0.02077 -0.0429 0.0869 1.0000
9.750 1.0627 0.03086 0.02276 -0.0411 0.0838 1.0000
10.000 1.0721 0.03232 0.02430 -0.0400 0.0815 1.0000
10.250 1.0806 0.03388 0.02591 -0.0388 0.0794 1.0000
10.500 1.0897 0.03541 0.02747 -0.0377 0.0775 1.0000
10.750 1.0997 0.03691 0.02899 -0.0367 0.0758 1.0000
11.000 1.1113 0.03834 0.03041 -0.0356 0.0741 1.0000
11.250 1.1283 0.03957 0.03157 -0.0347 0.0721 1.0000
11.500 1.1509 0.04052 0.03254 -0.0341 0.0705 1.0000
11.750 1.1685 0.04158 0.03369 -0.0335 0.0692 1.0000
12.000 1.1863 0.04268 0.03487 -0.0329 0.0673 1.0000
12.250 1.2022 0.04388 0.03613 -0.0323 0.0650 1.0000
12.500 1.2171 0.04516 0.03741 -0.0318 0.0622 1.0000
12.750 1.2435 0.04642 0.03865 -0.0318 0.0586 1.0000
13.000 1.2508 0.04792 0.04031 -0.0309 0.0570 1.0000
13.250 1.2622 0.04940 0.04191 -0.0301 0.0549 1.0000
13.500 1.2730 0.05093 0.04352 -0.0295 0.0529 1.0000
13.750 1.2872 0.05238 0.04495 -0.0291 0.0506 1.0000
14.000 1.3022 0.05428 0.04698 -0.0286 0.0480 1.0000
14.250 1.3018 0.05638 0.04928 -0.0277 0.0459 1.0000
14.500 1.3039 0.05844 0.05145 -0.0270 0.0437 1.0000
14.750 1.3101 0.06028 0.05327 -0.0267 0.0417 1.0000
15.000 1.3150 0.06299 0.05616 -0.0260 0.0391 1.0000
15.250 1.3134 0.06576 0.05914 -0.0255 0.0370 1.0000
15.500 1.3142 0.06830 0.06178 -0.0253 0.0353 1.0000
15.750 1.3286 0.07037 0.06376 -0.0251 0.0332 1.0000
16.000 1.3166 0.07430 0.06804 -0.0249 0.0321 1.0000
16.250 1.3095 0.07813 0.07213 -0.0250 0.0308 1.0000
16.500 1.3066 0.08152 0.07568 -0.0253 0.0297 1.0000
16.750 1.3048 0.08464 0.07890 -0.0258 0.0288 1.0000
17.000 1.3070 0.08731 0.08158 -0.0264 0.0279 1.0000
17.250 1.3065 0.09102 0.08537 -0.0269 0.0271 1.0000
17.500 1.2901 0.09664 0.09131 -0.0283 0.0267 1.0000
17.750 1.2717 0.10285 0.09784 -0.0303 0.0264 1.0000
18.000 1.2518 0.10959 0.10486 -0.0329 0.0261 1.0000
18.250 1.2301 0.11691 0.11247 -0.0361 0.0260 1.0000
18.500 1.2073 0.12482 0.12062 -0.0401 0.0259 1.0000
18.750 1.1819 0.13361 0.12966 -0.0450 0.0260 1.0000
19.000 1.1541 0.14345 0.13972 -0.0509 0.0262 1.0000
19.250 1.1258 0.15405 0.15051 -0.0577 0.0265 1.0000
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