FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-177 AIRFOIL (fx60177-il) Reynolds number: 50,000 Max Cl/Cd: 25.03 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60177-il-50000-n5.txt Download as CSV file: xf-fx60177-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-177 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5233 0.10658 0.09941 -0.0630 1.0001 0.0416
-12.500 -0.5595 0.09762 0.09039 -0.0666 1.0001 0.0401
-12.250 -0.6410 0.08505 0.07734 -0.0708 1.0001 0.0366
-12.000 -0.6644 0.08114 0.07332 -0.0699 1.0001 0.0365
-11.750 -0.6879 0.07760 0.06965 -0.0684 1.0001 0.0365
-11.500 -0.7111 0.07441 0.06630 -0.0662 1.0001 0.0366
-11.250 -0.7337 0.07156 0.06328 -0.0634 1.0001 0.0366
-11.000 -0.7507 0.06910 0.06076 -0.0605 1.0001 0.0370
-10.750 -0.7635 0.06708 0.05869 -0.0575 1.0001 0.0376
-10.500 -0.7780 0.06526 0.05680 -0.0540 1.0001 0.0382
-10.250 -0.7930 0.06357 0.05502 -0.0502 1.0001 0.0388
-10.000 -0.8040 0.06176 0.05309 -0.0469 1.0001 0.0398
-9.750 -0.8119 0.05972 0.05087 -0.0439 1.0001 0.0410
-9.500 -0.8170 0.05751 0.04840 -0.0410 1.0001 0.0425
-9.250 -0.8187 0.05517 0.04568 -0.0382 1.0001 0.0442
-9.000 -0.8141 0.05305 0.04338 -0.0360 1.0001 0.0463
-8.750 -0.8067 0.05146 0.04175 -0.0341 1.0001 0.0489
-8.500 -0.7960 0.04973 0.03982 -0.0321 1.0001 0.0519
-8.250 -0.7802 0.04801 0.03772 -0.0300 1.0001 0.0550
-8.000 -0.7648 0.04663 0.03647 -0.0284 1.0001 0.0589
-7.750 -0.7479 0.04550 0.03519 -0.0264 1.0001 0.0636
-7.500 -0.7270 0.04454 0.03411 -0.0244 1.0001 0.0683
-7.250 -0.7025 0.04362 0.03319 -0.0240 0.9976 0.0759
-7.000 -0.6790 0.04268 0.03222 -0.0237 0.9946 0.0841
-6.750 -0.6591 0.04162 0.03112 -0.0234 0.9908 0.0952
-6.500 -0.6417 0.04040 0.02995 -0.0232 0.9867 0.1101
-6.250 -0.6246 0.03900 0.02872 -0.0234 0.9825 0.1334
-6.000 -0.6123 0.03720 0.02730 -0.0233 0.9774 0.1730
-5.750 -0.6000 0.03491 0.02584 -0.0240 0.9730 0.2658
-5.500 -0.5867 0.03390 0.02593 -0.0223 0.9685 0.4132
-5.250 -0.5661 0.03519 0.02761 -0.0183 0.9638 0.5042
-5.000 -0.5385 0.03679 0.02912 -0.0163 0.9595 0.5621
-4.750 -0.5168 0.03830 0.03046 -0.0137 0.9541 0.6031
-4.500 -0.4932 0.03983 0.03178 -0.0114 0.9489 0.6328
-4.250 -0.4631 0.04135 0.03305 -0.0101 0.9447 0.6522
-4.000 -0.4430 0.04216 0.03368 -0.0078 0.9387 0.6693
-3.750 -0.4168 0.04295 0.03425 -0.0068 0.9333 0.6854
-3.250 -0.3687 0.04364 0.03455 -0.0053 0.9215 0.7122
-3.000 -0.3405 0.04365 0.03434 -0.0062 0.9163 0.7247
-2.750 -0.3181 0.04382 0.03437 -0.0050 0.9101 0.7317
-2.500 -0.2938 0.04368 0.03405 -0.0053 0.9039 0.7421
-2.250 -0.2647 0.04379 0.03399 -0.0057 0.8986 0.7502
-2.000 -0.2458 0.04359 0.03367 -0.0050 0.8907 0.7591
-1.750 -0.2127 0.04359 0.03350 -0.0063 0.8857 0.7665
-1.500 -0.1974 0.04334 0.03316 -0.0051 0.8769 0.7746
-1.250 -0.1657 0.04332 0.03301 -0.0061 0.8715 0.7814
-1.000 -0.1497 0.04313 0.03273 -0.0051 0.8630 0.7898
-0.750 -0.1196 0.04309 0.03258 -0.0057 0.8571 0.7961
-0.500 -0.1016 0.04290 0.03231 -0.0053 0.8486 0.8041
-0.250 -0.0714 0.04277 0.03210 -0.0059 0.8420 0.8091
0.000 -0.0514 0.04260 0.03186 -0.0054 0.8327 0.8155
0.250 -0.0198 0.04238 0.03156 -0.0067 0.8259 0.8213
0.500 -0.0017 0.04227 0.03141 -0.0055 0.8160 0.8270
0.750 0.0314 0.04205 0.03112 -0.0072 0.8099 0.8333
1.000 0.0474 0.04197 0.03103 -0.0057 0.7993 0.8385
1.250 0.0838 0.04166 0.03066 -0.0075 0.7935 0.8432
1.500 0.1007 0.04155 0.03053 -0.0066 0.7815 0.8488
1.750 0.1235 0.04135 0.03032 -0.0062 0.7714 0.8530
2.000 0.1555 0.04099 0.02994 -0.0071 0.7638 0.8572
2.250 0.1736 0.04095 0.02990 -0.0064 0.7521 0.8624
2.750 0.2272 0.04043 0.02940 -0.0067 0.7336 0.8707
3.000 0.2483 0.04031 0.02931 -0.0062 0.7217 0.8754
3.250 0.2871 0.03969 0.02869 -0.0080 0.7152 0.8793
3.500 0.3050 0.03960 0.02865 -0.0068 0.7019 0.8832
3.750 0.3260 0.03949 0.02858 -0.0062 0.6896 0.8873
4.000 0.3650 0.03865 0.02778 -0.0076 0.6834 0.8908
4.250 0.3873 0.03854 0.02771 -0.0073 0.6697 0.8946
4.500 0.4086 0.03828 0.02751 -0.0064 0.6564 0.8982
4.750 0.4338 0.03790 0.02720 -0.0060 0.6442 0.9020
5.000 0.4714 0.03698 0.02634 -0.0070 0.6364 0.9055
5.250 0.4952 0.03690 0.02634 -0.0068 0.6226 0.9092
5.500 0.5190 0.03663 0.02613 -0.0063 0.6094 0.9127
5.750 0.5465 0.03618 0.02575 -0.0061 0.5962 0.9165
6.000 0.5772 0.03562 0.02526 -0.0063 0.5827 0.9203
6.250 0.6079 0.03510 0.02478 -0.0065 0.5684 0.9240
6.500 0.6378 0.03454 0.02428 -0.0064 0.5536 0.9277
6.750 0.6693 0.03405 0.02382 -0.0067 0.5387 0.9315
7.000 0.6986 0.03383 0.02362 -0.0070 0.5226 0.9354
7.250 0.7233 0.03381 0.02366 -0.0067 0.5052 0.9392
7.500 0.7475 0.03384 0.02372 -0.0064 0.4874 0.9432
7.750 0.7713 0.03398 0.02387 -0.0062 0.4693 0.9475
8.000 0.7935 0.03422 0.02415 -0.0058 0.4508 0.9518
8.250 0.8156 0.03451 0.02446 -0.0055 0.4330 0.9561
8.500 0.8385 0.03487 0.02483 -0.0053 0.4163 0.9604
8.750 0.8606 0.03533 0.02534 -0.0052 0.4002 0.9647
9.000 0.8816 0.03589 0.02595 -0.0051 0.3846 0.9698
9.250 0.9028 0.03651 0.02663 -0.0051 0.3698 0.9752
9.500 0.9237 0.03715 0.02732 -0.0051 0.3553 0.9810
9.750 0.9431 0.03782 0.02805 -0.0050 0.3410 0.9884
10.000 0.9596 0.03834 0.02861 -0.0044 0.3278 0.9999
10.250 0.9804 0.03927 0.02959 -0.0046 0.3148 0.9999
10.500 0.9955 0.04054 0.03100 -0.0045 0.3021 0.9999
10.750 1.0130 0.04177 0.03236 -0.0046 0.2904 0.9999
11.000 1.0335 0.04285 0.03350 -0.0049 0.2793 0.9999
11.250 1.0519 0.04406 0.03479 -0.0052 0.2683 0.9999
11.500 1.0629 0.04577 0.03669 -0.0049 0.2578 0.9999
11.750 1.0783 0.04714 0.03814 -0.0050 0.2475 0.9999
12.000 1.0919 0.04857 0.03966 -0.0050 0.2373 0.9999
12.250 1.0974 0.05071 0.04200 -0.0046 0.2278 0.9999
12.500 1.1160 0.05195 0.04324 -0.0049 0.2189 0.9999
12.750 1.1165 0.05464 0.04623 -0.0046 0.2107 0.9999
13.000 1.1311 0.05623 0.04788 -0.0048 0.2028 0.9999
13.250 1.1292 0.05920 0.05111 -0.0046 0.1952 0.9999
13.500 1.1419 0.06091 0.05288 -0.0048 0.1879 0.9999
13.750 1.1353 0.06453 0.05681 -0.0049 0.1813 0.9999
14.000 1.1562 0.06549 0.05768 -0.0053 0.1742 0.9999
14.250 1.1354 0.07075 0.06335 -0.0057 0.1690 0.9999
14.500 1.1325 0.07420 0.06695 -0.0063 0.1628 0.9999
14.750 1.1320 0.07748 0.07034 -0.0071 0.1570 0.9999
15.000 1.1029 0.08470 0.07789 -0.0093 0.1527 0.9999
15.250 1.1039 0.08803 0.08131 -0.0105 0.1472 0.9999
15.500 1.0922 0.09345 0.08688 -0.0126 0.1430 0.9999
15.750 1.0001 0.11319 0.10699 -0.0221 0.1408 0.9999
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