FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 100,000 Max Cl/Cd: 30.19 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66182-il-100000-n5.txt Download as CSV file: xf-fx66182-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-182 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3159 0.09744 0.09273 -0.0733 0.8915 0.0273
-12.250 -0.3210 0.08691 0.08204 -0.0826 0.8672 0.0270
-12.000 -0.3364 0.07715 0.07205 -0.0914 0.8422 0.0266
-11.500 -0.3805 0.06317 0.05751 -0.1023 0.8000 0.0262
-11.250 -0.3999 0.05836 0.05242 -0.1049 0.7833 0.0262
-11.000 -0.4166 0.05432 0.04808 -0.1063 0.7691 0.0261
-10.500 -0.4441 0.04775 0.04090 -0.1065 0.7459 0.0263
-10.250 -0.4541 0.04521 0.03803 -0.1050 0.7366 0.0264
-10.000 -0.4600 0.04281 0.03525 -0.1031 0.7284 0.0268
-9.750 -0.4590 0.04040 0.03240 -0.1015 0.7210 0.0272
-9.500 -0.4488 0.03840 0.03019 -0.1007 0.7137 0.0279
-9.250 -0.4345 0.03717 0.02886 -0.1001 0.7071 0.0293
-9.000 -0.4196 0.03572 0.02720 -0.0994 0.7003 0.0305
-8.750 -0.4034 0.03412 0.02526 -0.0985 0.6948 0.0322
-8.500 -0.3844 0.03252 0.02331 -0.0977 0.6891 0.0334
-8.250 -0.3642 0.03111 0.02182 -0.0973 0.6838 0.0352
-8.000 -0.3440 0.03014 0.02075 -0.0967 0.6793 0.0374
-7.750 -0.3221 0.02909 0.01952 -0.0962 0.6747 0.0395
-7.500 -0.3000 0.02822 0.01843 -0.0955 0.6697 0.0418
-7.250 -0.2793 0.02714 0.01738 -0.0948 0.6654 0.0441
-7.000 -0.2584 0.02631 0.01648 -0.0940 0.6618 0.0461
-6.750 -0.2388 0.02558 0.01570 -0.0931 0.6572 0.0482
-6.500 -0.2187 0.02498 0.01497 -0.0921 0.6531 0.0514
-6.250 -0.2008 0.02424 0.01421 -0.0911 0.6497 0.0547
-6.000 -0.1813 0.02364 0.01351 -0.0901 0.6468 0.0584
-5.750 -0.1618 0.02309 0.01288 -0.0891 0.6432 0.0633
-5.500 -0.1432 0.02246 0.01226 -0.0882 0.6394 0.0719
-5.250 -0.1243 0.02178 0.01164 -0.0873 0.6360 0.0921
-5.000 -0.1071 0.02087 0.01100 -0.0864 0.6330 0.1493
-4.500 -0.0774 0.01897 0.01040 -0.0839 0.6270 0.4088
-4.250 -0.0547 0.01935 0.01104 -0.0824 0.6237 0.5031
-4.000 -0.0299 0.01998 0.01159 -0.0814 0.6208 0.5529
-3.750 -0.0047 0.02065 0.01213 -0.0802 0.6181 0.5828
-3.500 0.0212 0.02121 0.01257 -0.0791 0.6157 0.6015
-3.250 0.0460 0.02156 0.01282 -0.0782 0.6128 0.6157
-3.000 0.0702 0.02178 0.01293 -0.0775 0.6094 0.6282
-2.750 0.0954 0.02197 0.01307 -0.0768 0.6064 0.6348
-2.500 0.1215 0.02197 0.01288 -0.0768 0.6039 0.6430
-2.250 0.1480 0.02202 0.01281 -0.0766 0.6016 0.6474
-2.000 0.1753 0.02203 0.01267 -0.0766 0.5996 0.6521
-1.750 0.2003 0.02205 0.01259 -0.0767 0.5966 0.6574
-1.500 0.2250 0.02210 0.01259 -0.0765 0.5934 0.6613
-1.250 0.2504 0.02217 0.01259 -0.0763 0.5905 0.6648
-1.000 0.2768 0.02221 0.01254 -0.0763 0.5882 0.6690
-0.750 0.3042 0.02223 0.01242 -0.0767 0.5861 0.6738
-0.500 0.3318 0.02226 0.01235 -0.0769 0.5842 0.6772
-0.250 0.3561 0.02240 0.01248 -0.0766 0.5814 0.6804
0.000 0.3795 0.02259 0.01267 -0.0763 0.5782 0.6842
0.250 0.4048 0.02273 0.01277 -0.0764 0.5754 0.6882
0.500 0.4309 0.02286 0.01284 -0.0765 0.5731 0.6917
0.750 0.4572 0.02297 0.01292 -0.0765 0.5711 0.6946
1.000 0.4847 0.02305 0.01295 -0.0767 0.5692 0.6979
1.250 0.5117 0.02319 0.01303 -0.0769 0.5672 0.7015
1.500 0.5319 0.02359 0.01349 -0.0764 0.5635 0.7053
1.750 0.5544 0.02388 0.01384 -0.0760 0.5606 0.7084
2.000 0.5784 0.02413 0.01412 -0.0757 0.5582 0.7116
2.250 0.6043 0.02433 0.01431 -0.0758 0.5561 0.7149
2.500 0.6321 0.02449 0.01444 -0.0762 0.5543 0.7187
2.750 0.6610 0.02460 0.01451 -0.0767 0.5526 0.7225
3.000 0.6767 0.02521 0.01526 -0.0754 0.5489 0.7258
3.250 0.6947 0.02577 0.01592 -0.0744 0.5455 0.7294
3.500 0.7168 0.02618 0.01638 -0.0741 0.5429 0.7332
4.000 0.7687 0.02661 0.01685 -0.0742 0.5388 0.7410
4.250 0.7973 0.02673 0.01699 -0.0745 0.5372 0.7452
4.500 0.8035 0.02789 0.01833 -0.0723 0.5326 0.7499
4.750 0.8168 0.02873 0.01928 -0.0709 0.5287 0.7542
5.000 0.8384 0.02913 0.01977 -0.0704 0.5260 0.7584
5.250 0.8644 0.02936 0.02005 -0.0704 0.5241 0.7636
5.500 0.8924 0.02956 0.02030 -0.0708 0.5225 0.7694
6.000 0.8842 0.03285 0.02392 -0.0642 0.5120 0.7820
6.250 0.9057 0.03324 0.02442 -0.0637 0.5097 0.7885
6.500 0.9327 0.03339 0.02466 -0.0638 0.5080 0.7961
6.750 0.9614 0.03351 0.02488 -0.0641 0.5068 0.8049
8.250 0.8579 0.05345 0.04562 -0.0496 0.4594 1.0000
8.750 0.8748 0.05711 0.04937 -0.0490 0.4488 1.0000
9.000 0.8563 0.06154 0.05383 -0.0483 0.4386 1.0000
9.250 0.8776 0.06214 0.05450 -0.0482 0.4357 1.0000
9.500 0.9033 0.06230 0.05474 -0.0482 0.4338 1.0000
9.750 0.9312 0.06220 0.05472 -0.0481 0.4325 1.0000
10.250 0.9372 0.06678 0.05945 -0.0474 0.4188 1.0000
11.250 0.9616 0.07477 0.06780 -0.0463 0.3921 1.0000
11.500 0.9899 0.07423 0.06739 -0.0459 0.3900 1.0000
12.000 1.0092 0.07715 0.07054 -0.0453 0.3761 1.0000
12.250 1.0043 0.08032 0.07379 -0.0452 0.3651 1.0000
12.500 1.0421 0.07773 0.07135 -0.0444 0.3614 1.0000
13.000 1.0598 0.07965 0.07346 -0.0435 0.3361 1.0000
13.250 1.0736 0.08006 0.07397 -0.0431 0.3211 1.0000
13.500 1.0868 0.08079 0.07477 -0.0428 0.3042 1.0000
13.750 1.0961 0.08230 0.07634 -0.0427 0.2859 1.0000
14.000 1.1074 0.08360 0.07767 -0.0425 0.2663 1.0000
14.250 1.1370 0.08182 0.07565 -0.0414 0.2301 1.0000
14.500 1.1400 0.08396 0.07747 -0.0411 0.1917 1.0000
14.750 1.1320 0.08788 0.08111 -0.0414 0.1583 1.0000
15.000 1.1225 0.09225 0.08529 -0.0420 0.1310 1.0000
15.250 1.1135 0.09672 0.08959 -0.0427 0.1070 1.0000
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Polar data table (+)
Polar graphs
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