FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 50,000 Max Cl/Cd: 22.66 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60160-il-50000-n5.txt Download as CSV file: xf-fx60160-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3991 0.10950 0.10228 -0.0596 1.0000 0.0728
-11.000 -0.4079 0.10532 0.09817 -0.0602 1.0000 0.0725
-10.750 -0.4206 0.10067 0.09362 -0.0611 1.0000 0.0724
-10.500 -0.4366 0.09570 0.08874 -0.0622 1.0000 0.0720
-10.250 -0.4572 0.09089 0.08401 -0.0630 1.0000 0.0715
-10.000 -0.4838 0.08640 0.07962 -0.0633 1.0000 0.0708
-9.750 -0.5149 0.08262 0.07591 -0.0625 1.0000 0.0700
-9.500 -0.5505 0.07968 0.07303 -0.0606 1.0000 0.0693
-9.250 -0.5895 0.07745 0.07086 -0.0573 1.0000 0.0683
-9.000 -0.6068 0.07238 0.06557 -0.0611 0.9915 0.0681
-8.750 -0.6096 0.06729 0.06014 -0.0650 0.9816 0.0685
-8.500 -0.6060 0.06276 0.05522 -0.0679 0.9727 0.0691
-8.250 -0.6002 0.05888 0.05094 -0.0693 0.9639 0.0693
-8.000 -0.5871 0.05517 0.04677 -0.0710 0.9569 0.0698
-7.750 -0.5737 0.05210 0.04326 -0.0717 0.9492 0.0707
-7.500 -0.5531 0.04924 0.03983 -0.0732 0.9435 0.0728
-7.250 -0.5372 0.04702 0.03705 -0.0729 0.9357 0.0744
-7.000 -0.5103 0.04458 0.03433 -0.0742 0.9310 0.0758
-6.750 -0.4884 0.04275 0.03232 -0.0742 0.9250 0.0771
-6.500 -0.4635 0.04117 0.03056 -0.0744 0.9193 0.0789
-6.250 -0.4324 0.03978 0.02895 -0.0756 0.9152 0.0824
-6.000 -0.4112 0.03871 0.02766 -0.0748 0.9086 0.0857
-5.750 -0.3829 0.03766 0.02635 -0.0748 0.9036 0.0880
-5.500 -0.3503 0.03661 0.02532 -0.0753 0.9001 0.0907
-5.250 -0.3316 0.03600 0.02469 -0.0738 0.8934 0.0943
-5.000 -0.3052 0.03537 0.02394 -0.0737 0.8882 0.0998
-4.750 -0.2747 0.03460 0.02312 -0.0743 0.8846 0.1054
-4.500 -0.2621 0.03411 0.02261 -0.0722 0.8768 0.1094
-4.250 -0.2348 0.03343 0.02181 -0.0726 0.8720 0.1175
-4.000 -0.2156 0.03276 0.02116 -0.0721 0.8660 0.1284
-3.750 -0.1950 0.03200 0.02043 -0.0719 0.8599 0.1434
-3.500 -0.1662 0.03048 0.01926 -0.0737 0.8560 0.1881
-3.250 -0.1647 0.02933 0.02003 -0.0696 0.8486 0.4675
-3.000 -0.1438 0.03016 0.02092 -0.0668 0.8432 0.5731
-2.750 -0.1206 0.03098 0.02157 -0.0649 0.8380 0.6212
-2.500 -0.1100 0.03199 0.02252 -0.0605 0.8305 0.6566
-2.250 -0.0889 0.03280 0.02323 -0.0573 0.8261 0.6904
-2.000 -0.0796 0.03336 0.02372 -0.0532 0.8186 0.7145
-1.750 -0.0622 0.03368 0.02395 -0.0501 0.8131 0.7353
-1.500 -0.0317 0.03360 0.02368 -0.0503 0.8095 0.7490
-1.250 -0.0201 0.03375 0.02370 -0.0485 0.8009 0.7586
-1.000 0.0073 0.03365 0.02346 -0.0485 0.7962 0.7666
-0.750 0.0353 0.03357 0.02320 -0.0490 0.7914 0.7763
-0.500 0.0487 0.03375 0.02331 -0.0470 0.7833 0.7847
-0.250 0.0799 0.03360 0.02303 -0.0478 0.7791 0.7935
0.000 0.0962 0.03379 0.02313 -0.0465 0.7716 0.8016
0.250 0.1210 0.03381 0.02306 -0.0465 0.7655 0.8091
0.500 0.1556 0.03361 0.02275 -0.0478 0.7619 0.8162
0.750 0.1660 0.03405 0.02314 -0.0460 0.7525 0.8236
1.000 0.1967 0.03395 0.02298 -0.0467 0.7477 0.8303
1.250 0.2181 0.03419 0.02316 -0.0464 0.7408 0.8374
1.500 0.2400 0.03436 0.02330 -0.0459 0.7337 0.8441
1.750 0.2759 0.03419 0.02307 -0.0475 0.7300 0.8509
2.000 0.2854 0.03480 0.02370 -0.0455 0.7200 0.8580
2.250 0.3183 0.03473 0.02360 -0.0466 0.7154 0.8649
2.500 0.3342 0.03522 0.02411 -0.0456 0.7068 0.8722
2.750 0.3623 0.03535 0.02424 -0.0461 0.7008 0.8796
3.000 0.4001 0.03507 0.02398 -0.0476 0.6975 0.8864
3.250 0.4085 0.03603 0.02500 -0.0461 0.6863 0.8958
3.500 0.4464 0.03581 0.02483 -0.0477 0.6825 0.9035
4.000 0.4986 0.03667 0.02585 -0.0490 0.6675 0.9246
4.250 0.5192 0.03769 0.02698 -0.0498 0.6570 0.9402
4.500 0.5614 0.03762 0.02703 -0.0526 0.6523 0.9680
5.000 0.6064 0.03886 0.02836 -0.0533 0.6367 1.0000
5.500 0.6516 0.04031 0.02993 -0.0540 0.6213 1.0000
6.000 0.6958 0.04189 0.03166 -0.0545 0.6057 1.0000
6.500 0.7383 0.04360 0.03355 -0.0548 0.5900 1.0000
6.750 0.7454 0.04546 0.03548 -0.0541 0.5788 1.0000
7.000 0.7789 0.04544 0.03561 -0.0548 0.5743 1.0000
7.250 0.7843 0.04748 0.03773 -0.0539 0.5628 1.0000
7.500 0.8191 0.04726 0.03766 -0.0545 0.5585 1.0000
8.250 0.8949 0.04625 0.03706 -0.0521 0.5245 1.0000
8.500 0.9261 0.04465 0.03560 -0.0508 0.5093 1.0000
8.750 0.9486 0.04405 0.03516 -0.0494 0.4936 1.0000
9.000 0.9614 0.04432 0.03555 -0.0476 0.4751 1.0000
9.250 0.9787 0.04409 0.03544 -0.0458 0.4548 1.0000
9.500 0.9943 0.04388 0.03529 -0.0439 0.4293 1.0000
9.750 1.0031 0.04444 0.03589 -0.0419 0.3969 1.0000
10.000 1.0101 0.04543 0.03688 -0.0401 0.3611 1.0000
10.250 1.0166 0.04653 0.03784 -0.0382 0.3096 1.0000
10.500 1.0173 0.04819 0.03894 -0.0360 0.2296 1.0000
10.750 1.0069 0.05145 0.04165 -0.0343 0.1798 1.0000
11.000 0.9986 0.05491 0.04482 -0.0333 0.1530 1.0000
11.250 0.9941 0.05817 0.04792 -0.0325 0.1372 1.0000
11.500 0.9930 0.06117 0.05084 -0.0320 0.1266 1.0000
11.750 0.9929 0.06412 0.05371 -0.0315 0.1193 1.0000
12.000 0.9974 0.06660 0.05624 -0.0311 0.1127 1.0000
12.250 1.0020 0.06906 0.05867 -0.0306 0.1081 1.0000
12.500 1.0118 0.07097 0.06063 -0.0300 0.1044 1.0000
12.750 1.0245 0.07257 0.06233 -0.0293 0.1008 1.0000
13.000 1.0398 0.07389 0.06370 -0.0286 0.0976 1.0000
13.250 1.0612 0.07457 0.06430 -0.0274 0.0940 1.0000
13.500 1.0812 0.07571 0.06571 -0.0267 0.0905 1.0000
13.750 1.1044 0.07664 0.06682 -0.0259 0.0867 1.0000
14.000 1.1408 0.07668 0.06697 -0.0248 0.0836 1.0000
14.250 1.1860 0.07700 0.06735 -0.0239 0.0799 1.0000
14.500 1.1896 0.08013 0.07087 -0.0237 0.0778 1.0000
14.750 1.1938 0.08338 0.07445 -0.0236 0.0755 1.0000
15.000 1.1979 0.08680 0.07816 -0.0236 0.0735 1.0000
15.250 1.2003 0.09019 0.08173 -0.0237 0.0709 1.0000
15.500 1.2103 0.09324 0.08477 -0.0238 0.0672 1.0000
15.750 1.1889 0.09855 0.09044 -0.0250 0.0663 1.0000
16.000 1.1679 0.10437 0.09660 -0.0268 0.0654 1.0000
16.250 1.1460 0.11082 0.10335 -0.0293 0.0646 1.0000
16.500 1.1222 0.11805 0.11085 -0.0326 0.0641 1.0000
16.750 1.0953 0.12647 0.11951 -0.0371 0.0640 1.0000
17.000 1.0645 0.13658 0.12982 -0.0430 0.0645 1.0000
17.250 1.0311 0.14860 0.14199 -0.0505 0.0654 1.0000
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