FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 50,000 Max Cl/Cd: 8.27 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617a2-il-50000-n5.txt Download as CSV file: xf-fx6617a2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-17AII-182 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2922 0.11900 0.11268 -0.0583 1.0000 0.0542
-12.000 -0.2955 0.11468 0.10849 -0.0599 1.0000 0.0539
-11.750 -0.3010 0.11029 0.10425 -0.0615 1.0000 0.0540
-11.500 -0.3024 0.10446 0.09855 -0.0652 0.9864 0.0536
-11.250 -0.3016 0.09651 0.09061 -0.0723 0.9409 0.0532
-11.000 -0.3116 0.08622 0.08026 -0.0819 0.9189 0.0521
-10.750 -0.3379 0.07538 0.06921 -0.0928 0.9000 0.0507
-10.500 -0.3886 0.06555 0.05879 -0.1029 0.8774 0.0482
-10.250 -0.3903 0.06147 0.05443 -0.1060 0.8576 0.0488
-10.000 -0.3986 0.05822 0.05085 -0.1067 0.8403 0.0490
-9.750 -0.4007 0.05548 0.04784 -0.1065 0.8261 0.0496
-9.500 -0.4000 0.05284 0.04488 -0.1059 0.8140 0.0501
-9.250 -0.3943 0.05056 0.04231 -0.1053 0.8036 0.0514
-9.000 -0.3889 0.04845 0.03992 -0.1042 0.7932 0.0531
-8.750 -0.3806 0.04629 0.03736 -0.1033 0.7848 0.0551
-8.500 -0.3699 0.04419 0.03484 -0.1021 0.7761 0.0568
-8.250 -0.3528 0.04208 0.03221 -0.1013 0.7692 0.0583
-8.000 -0.3321 0.04033 0.03037 -0.1008 0.7615 0.0610
-7.750 -0.3088 0.03895 0.02882 -0.1004 0.7557 0.0648
-7.500 -0.2829 0.03765 0.02729 -0.0998 0.7488 0.0681
-7.250 -0.2506 0.03646 0.02583 -0.0994 0.7431 0.0715
-7.000 -0.2264 0.03551 0.02487 -0.0987 0.7379 0.0766
-6.750 -0.2071 0.03483 0.02406 -0.0974 0.7316 0.0830
-6.500 -0.1905 0.03400 0.02322 -0.0959 0.7265 0.0888
-6.250 -0.1755 0.03321 0.02232 -0.0942 0.7221 0.0968
-5.750 -0.1571 0.03149 0.02077 -0.0906 0.7117 0.1264
-5.500 -0.1502 0.03014 0.01973 -0.0888 0.7078 0.1663
-5.250 -0.1501 0.02882 0.01908 -0.0864 0.7026 0.2579
-5.000 -0.1423 0.02925 0.02085 -0.0812 0.6979 0.4437
-4.750 -0.1253 0.03032 0.02174 -0.0785 0.6940 0.5322
-4.500 -0.1059 0.03172 0.02289 -0.0753 0.6908 0.5806
-4.250 -0.0895 0.03312 0.02422 -0.0716 0.6856 0.6080
-4.000 -0.0720 0.03379 0.02470 -0.0690 0.6814 0.6309
-3.750 -0.0496 0.03419 0.02488 -0.0671 0.6780 0.6477
-3.500 -0.0277 0.03428 0.02470 -0.0658 0.6749 0.6620
-3.250 -0.0145 0.03467 0.02502 -0.0636 0.6700 0.6713
-3.000 0.0021 0.03481 0.02499 -0.0622 0.6660 0.6814
-2.750 0.0209 0.03478 0.02475 -0.0612 0.6627 0.6928
-2.500 0.0462 0.03480 0.02457 -0.0604 0.6601 0.7011
-2.250 0.0539 0.03518 0.02489 -0.0582 0.6551 0.7107
-2.000 0.0680 0.03547 0.02508 -0.0565 0.6508 0.7188
-1.750 0.0872 0.03552 0.02496 -0.0558 0.6476 0.7263
-1.500 0.1111 0.03551 0.02479 -0.0554 0.6450 0.7323
-1.250 0.1210 0.03593 0.02511 -0.0541 0.6407 0.7395
-1.000 0.1293 0.03653 0.02569 -0.0520 0.6356 0.7445
-0.750 0.1488 0.03677 0.02579 -0.0515 0.6322 0.7506
-0.500 0.1730 0.03685 0.02571 -0.0517 0.6297 0.7564
-0.250 0.1956 0.03705 0.02580 -0.0513 0.6272 0.7613
0.000 0.1844 0.03852 0.02732 -0.0477 0.6201 0.7673
0.250 0.2024 0.03894 0.02764 -0.0473 0.6165 0.7725
0.500 0.2270 0.03915 0.02775 -0.0472 0.6140 0.7772
0.750 0.2555 0.03928 0.02776 -0.0478 0.6121 0.7824
1.000 0.2293 0.04164 0.03019 -0.0433 0.6036 0.7881
1.250 0.2483 0.04215 0.03064 -0.0428 0.6002 0.7930
1.500 0.2749 0.04244 0.03084 -0.0432 0.5979 0.7984
2.000 0.2676 0.04588 0.03430 -0.0391 0.5865 0.8096
2.250 0.2908 0.04645 0.03480 -0.0393 0.5836 0.8155
2.500 0.3195 0.04675 0.03505 -0.0399 0.5815 0.8211
2.750 0.3063 0.04931 0.03765 -0.0378 0.5744 0.8278
3.000 0.3211 0.05044 0.03876 -0.0377 0.5703 0.8345
3.250 0.3454 0.05105 0.03937 -0.0381 0.5675 0.8412
3.500 0.3744 0.05151 0.03980 -0.0388 0.5654 0.8490
3.750 0.3644 0.05407 0.04245 -0.0375 0.5585 0.8579
4.000 0.3817 0.05522 0.04363 -0.0378 0.5544 0.8675
4.250 0.4088 0.05593 0.04438 -0.0388 0.5516 0.8786
4.500 0.4416 0.05656 0.04507 -0.0404 0.5495 0.8924
5.000 0.4618 0.06071 0.04943 -0.0430 0.5384 1.0000
5.250 0.4876 0.06170 0.05039 -0.0441 0.5356 1.0000
5.500 0.5175 0.06254 0.05120 -0.0454 0.5336 1.0000
5.750 0.5036 0.06574 0.05440 -0.0447 0.5263 1.0000
6.000 0.5222 0.06715 0.05579 -0.0453 0.5225 1.0000
6.250 0.5480 0.06820 0.05684 -0.0462 0.5197 1.0000
6.500 0.5547 0.07032 0.05896 -0.0462 0.5149 1.0000
6.750 0.5606 0.07243 0.06108 -0.0462 0.5095 1.0000
7.000 0.5818 0.07371 0.06236 -0.0467 0.5059 1.0000
7.250 0.6097 0.07463 0.06331 -0.0474 0.5034 1.0000
7.500 0.6013 0.07755 0.06626 -0.0468 0.4960 1.0000
7.750 0.6189 0.07899 0.06773 -0.0471 0.4916 1.0000
8.000 0.6449 0.08000 0.06877 -0.0476 0.4887 1.0000
8.250 0.6409 0.08271 0.07153 -0.0472 0.4816 1.0000
8.500 0.6566 0.08428 0.07317 -0.0474 0.4769 1.0000
8.750 0.6819 0.08532 0.07427 -0.0477 0.4738 1.0000
9.000 0.6780 0.08807 0.07707 -0.0474 0.4662 1.0000
9.250 0.6955 0.08951 0.07859 -0.0476 0.4614 1.0000
9.500 0.7225 0.09040 0.07957 -0.0479 0.4584 1.0000
9.750 0.7147 0.09342 0.08267 -0.0476 0.4495 1.0000
10.000 0.7374 0.09449 0.08383 -0.0477 0.4452 1.0000
10.250 0.7401 0.09692 0.08634 -0.0477 0.4379 1.0000
10.500 0.7555 0.09843 0.08798 -0.0477 0.4320 1.0000
10.750 0.7833 0.09910 0.08877 -0.0478 0.4287 1.0000
11.000 0.7757 0.10225 0.09201 -0.0478 0.4187 1.0000
11.250 0.8019 0.10292 0.09281 -0.0478 0.4147 1.0000
11.500 0.7974 0.10591 0.09590 -0.0479 0.4050 1.0000
11.750 0.8230 0.10648 0.09664 -0.0478 0.4005 1.0000
12.000 0.8198 0.10943 0.09969 -0.0479 0.3906 1.0000
12.250 0.8460 0.10979 0.10021 -0.0477 0.3858 1.0000
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