FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.85 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s171-il-1000000-n5.txt Download as CSV file: xf-fx66s171-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.6727 0.12102 0.11888 -0.0357 1.0000 0.0051
-17.250 -0.7291 0.10560 0.10327 -0.0436 1.0000 0.0050
-17.000 -0.7657 0.09461 0.09212 -0.0494 1.0000 0.0050
-16.750 -0.7988 0.08466 0.08201 -0.0549 1.0000 0.0049
-16.500 -0.8224 0.07675 0.07395 -0.0594 1.0000 0.0049
-16.250 -0.8406 0.07001 0.06710 -0.0633 1.0000 0.0050
-16.000 -0.8538 0.06439 0.06136 -0.0666 1.0000 0.0050
-15.750 -0.8682 0.05885 0.05570 -0.0697 1.0000 0.0049
-15.500 -0.8758 0.05457 0.05134 -0.0720 1.0000 0.0050
-15.250 -0.8700 0.04934 0.04596 -0.0784 0.9492 0.0050
-15.000 -0.7758 0.04254 0.03852 -0.1049 0.8407 0.0052
-14.750 -0.7827 0.03961 0.03530 -0.1056 0.7913 0.0053
-14.500 -0.7834 0.03737 0.03284 -0.1059 0.7565 0.0053
-14.250 -0.7841 0.03504 0.03036 -0.1064 0.7349 0.0053
-14.000 -0.7833 0.03289 0.02808 -0.1066 0.7177 0.0054
-13.750 -0.7816 0.03086 0.02591 -0.1068 0.7031 0.0054
-13.500 -0.7803 0.02882 0.02375 -0.1068 0.6908 0.0054
-13.250 -0.7737 0.02731 0.02213 -0.1067 0.6789 0.0055
-13.000 -0.7712 0.02547 0.02018 -0.1065 0.6685 0.0056
-12.750 -0.7650 0.02404 0.01865 -0.1062 0.6595 0.0056
-12.500 -0.7586 0.02277 0.01728 -0.1055 0.6507 0.0057
-12.250 -0.7576 0.02145 0.01586 -0.1040 0.6435 0.0058
-12.000 -0.7554 0.02060 0.01491 -0.1014 0.6363 0.0059
-11.750 -0.7445 0.01992 0.01414 -0.0998 0.6296 0.0060
-11.500 -0.7304 0.01922 0.01335 -0.0985 0.6228 0.0061
-11.250 -0.7142 0.01861 0.01264 -0.0974 0.6165 0.0062
-11.000 -0.6959 0.01804 0.01199 -0.0965 0.6105 0.0063
-10.750 -0.6761 0.01755 0.01143 -0.0958 0.6042 0.0064
-10.500 -0.6571 0.01694 0.01074 -0.0949 0.5993 0.0066
-10.250 -0.6373 0.01632 0.01005 -0.0942 0.5940 0.0069
-10.000 -0.6160 0.01582 0.00947 -0.0936 0.5887 0.0071
-9.750 -0.5936 0.01537 0.00896 -0.0931 0.5843 0.0073
-9.500 -0.5704 0.01495 0.00849 -0.0927 0.5797 0.0075
-9.250 -0.5468 0.01456 0.00804 -0.0923 0.5751 0.0078
-9.000 -0.5227 0.01421 0.00762 -0.0919 0.5709 0.0081
-8.750 -0.4980 0.01384 0.00721 -0.0916 0.5671 0.0084
-8.500 -0.4730 0.01352 0.00682 -0.0914 0.5628 0.0087
-8.250 -0.4481 0.01318 0.00643 -0.0911 0.5587 0.0091
-8.000 -0.4229 0.01286 0.00606 -0.0909 0.5551 0.0098
-7.750 -0.3970 0.01257 0.00575 -0.0908 0.5516 0.0105
-7.500 -0.3708 0.01231 0.00545 -0.0907 0.5477 0.0113
-7.250 -0.3446 0.01205 0.00514 -0.0905 0.5438 0.0124
-7.000 -0.3183 0.01181 0.00487 -0.0904 0.5401 0.0136
-6.750 -0.2914 0.01160 0.00463 -0.0904 0.5368 0.0149
-6.500 -0.2646 0.01137 0.00438 -0.0904 0.5334 0.0166
-6.250 -0.2376 0.01117 0.00414 -0.0903 0.5303 0.0185
-5.750 -0.1833 0.01079 0.00372 -0.0903 0.5249 0.0227
-5.500 -0.1558 0.01062 0.00352 -0.0904 0.5226 0.0251
-5.250 -0.1283 0.01043 0.00333 -0.0904 0.5202 0.0295
-5.000 -0.1009 0.01024 0.00315 -0.0905 0.5175 0.0355
-4.750 -0.0736 0.01006 0.00298 -0.0905 0.5146 0.0452
-4.250 -0.0189 0.00964 0.00264 -0.0906 0.5096 0.0776
-4.000 0.0087 0.00941 0.00248 -0.0908 0.5076 0.1021
-3.750 0.0359 0.00912 0.00231 -0.0909 0.5055 0.1395
-3.500 0.0630 0.00881 0.00214 -0.0910 0.5033 0.1848
-3.250 0.0898 0.00846 0.00197 -0.0911 0.5010 0.2407
-3.000 0.1167 0.00813 0.00184 -0.0912 0.4990 0.3103
-2.750 0.1441 0.00794 0.00176 -0.0913 0.4970 0.3528
-2.500 0.1723 0.00783 0.00172 -0.0914 0.4954 0.3795
-2.250 0.2009 0.00775 0.00169 -0.0916 0.4940 0.4017
-2.000 0.2295 0.00770 0.00170 -0.0918 0.4924 0.4302
-1.750 0.2583 0.00769 0.00170 -0.0920 0.4906 0.4437
-1.500 0.2870 0.00769 0.00170 -0.0922 0.4884 0.4519
-1.000 0.3444 0.00773 0.00171 -0.0926 0.4841 0.4673
-0.750 0.3729 0.00777 0.00172 -0.0928 0.4821 0.4725
-0.500 0.4017 0.00781 0.00172 -0.0930 0.4802 0.4755
-0.250 0.4306 0.00781 0.00173 -0.0932 0.4786 0.4785
0.000 0.4594 0.00782 0.00175 -0.0935 0.4768 0.4817
0.250 0.4882 0.00784 0.00176 -0.0937 0.4748 0.4848
0.500 0.5169 0.00787 0.00178 -0.0939 0.4730 0.4878
0.750 0.5455 0.00792 0.00181 -0.0941 0.4709 0.4904
1.000 0.5739 0.00795 0.00183 -0.0943 0.4689 0.4931
1.250 0.6021 0.00800 0.00187 -0.0944 0.4665 0.4960
1.500 0.6306 0.00803 0.00192 -0.0947 0.4650 0.4990
1.750 0.6593 0.00806 0.00196 -0.0949 0.4635 0.5021
2.000 0.6879 0.00810 0.00201 -0.0951 0.4618 0.5052
2.250 0.7163 0.00813 0.00206 -0.0953 0.4600 0.5081
2.500 0.7446 0.00817 0.00211 -0.0955 0.4582 0.5114
2.750 0.7728 0.00822 0.00218 -0.0957 0.4563 0.5147
3.000 0.8009 0.00828 0.00224 -0.0958 0.4543 0.5178
3.250 0.8288 0.00835 0.00232 -0.0960 0.4524 0.5210
3.500 0.8568 0.00840 0.00240 -0.0961 0.4506 0.5247
3.750 0.8850 0.00844 0.00248 -0.0963 0.4488 0.5292
4.000 0.9132 0.00848 0.00256 -0.0965 0.4465 0.5334
4.250 0.9412 0.00854 0.00265 -0.0967 0.4442 0.5374
4.500 0.9688 0.00860 0.00274 -0.0968 0.4415 0.5425
4.750 0.9961 0.00868 0.00284 -0.0968 0.4385 0.5489
5.000 1.0234 0.00876 0.00295 -0.0969 0.4359 0.5542
5.250 1.0513 0.00880 0.00307 -0.0970 0.4338 0.5610
5.500 1.0790 0.00887 0.00318 -0.0972 0.4313 0.5668
5.750 1.1064 0.00893 0.00329 -0.0972 0.4286 0.5725
6.000 1.1334 0.00901 0.00342 -0.0973 0.4256 0.5791
6.250 1.1599 0.00912 0.00356 -0.0972 0.4224 0.5860
6.500 1.1871 0.00918 0.00370 -0.0973 0.4194 0.5945
6.750 1.2142 0.00926 0.00385 -0.0973 0.4162 0.6040
7.000 1.2407 0.00935 0.00400 -0.0973 0.4122 0.6155
7.250 1.2663 0.00947 0.00416 -0.0971 0.4063 0.6280
7.500 1.2903 0.00964 0.00434 -0.0966 0.3924 0.6411
7.750 1.3116 0.00996 0.00462 -0.0957 0.3697 0.6554
8.000 1.3274 0.01056 0.00507 -0.0940 0.3342 0.6723
8.500 1.3510 0.01202 0.00626 -0.0891 0.2636 0.7167
8.750 1.3489 0.01315 0.00720 -0.0845 0.2131 0.7518
9.000 1.3430 0.01398 0.00803 -0.0789 0.1819 0.8102
9.250 1.3349 0.01504 0.00920 -0.0735 0.1440 1.0000
9.500 1.3252 0.01643 0.01046 -0.0684 0.1154 1.0000
9.750 1.3193 0.01789 0.01183 -0.0645 0.0944 1.0000
10.000 1.3119 0.01970 0.01357 -0.0611 0.0758 1.0000
10.250 1.3082 0.02160 0.01544 -0.0586 0.0611 1.0000
10.500 1.3024 0.02391 0.01771 -0.0565 0.0464 1.0000
10.750 1.3019 0.02602 0.01981 -0.0551 0.0378 1.0000
11.000 1.3015 0.02823 0.02203 -0.0539 0.0303 1.0000
11.250 1.3004 0.03058 0.02438 -0.0527 0.0239 1.0000
11.500 1.3011 0.03283 0.02666 -0.0518 0.0199 1.0000
11.750 1.3018 0.03512 0.02896 -0.0510 0.0167 1.0000
12.000 1.3041 0.03729 0.03118 -0.0502 0.0146 1.0000
12.250 1.3059 0.03955 0.03347 -0.0496 0.0131 1.0000
12.500 1.3075 0.04185 0.03581 -0.0490 0.0114 1.0000
12.750 1.3100 0.04415 0.03815 -0.0485 0.0105 1.0000
13.000 1.3123 0.04652 0.04056 -0.0480 0.0096 1.0000
13.250 1.3163 0.04877 0.04285 -0.0477 0.0089 1.0000
13.500 1.3195 0.05115 0.04528 -0.0475 0.0083 1.0000
13.750 1.3228 0.05356 0.04774 -0.0473 0.0078 1.0000
14.000 1.3248 0.05616 0.05039 -0.0472 0.0071 1.0000
14.250 1.3291 0.05854 0.05282 -0.0471 0.0068 1.0000
14.500 1.3329 0.06102 0.05534 -0.0471 0.0064 1.0000
14.750 1.3361 0.06361 0.05798 -0.0472 0.0060 1.0000
15.000 1.3394 0.06622 0.06064 -0.0473 0.0057 1.0000
15.250 1.3414 0.06901 0.06347 -0.0475 0.0054 1.0000
15.500 1.3445 0.07171 0.06623 -0.0477 0.0050 1.0000
15.750 1.3478 0.07444 0.06901 -0.0480 0.0049 1.0000
16.000 1.3510 0.07720 0.07184 -0.0483 0.0047 1.0000
16.250 1.3544 0.07997 0.07467 -0.0487 0.0045 1.0000
16.500 1.3564 0.08295 0.07770 -0.0492 0.0042 1.0000
16.750 1.3595 0.08582 0.08062 -0.0497 0.0040 1.0000
17.000 1.3607 0.08900 0.08385 -0.0503 0.0039 1.0000
17.250 1.3617 0.09224 0.08715 -0.0510 0.0036 1.0000
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