FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 200,000 Max Cl/Cd: 59.69 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s196-il-200000-n5.txt Download as CSV file: xf-fx66s196-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4044 0.08741 0.08302 -0.0979 0.8204 0.0167
-14.750 -0.4295 0.07828 0.07368 -0.1040 0.8113 0.0164
-14.500 -0.4615 0.06938 0.06447 -0.1098 0.8025 0.0165
-14.250 -0.4863 0.06300 0.05782 -0.1133 0.7925 0.0167
-14.000 -0.5003 0.05866 0.05324 -0.1151 0.7821 0.0166
-13.750 -0.5169 0.05437 0.04867 -0.1165 0.7725 0.0168
-13.500 -0.5284 0.05081 0.04483 -0.1173 0.7641 0.0169
-13.250 -0.5372 0.04770 0.04142 -0.1176 0.7560 0.0171
-13.000 -0.5416 0.04498 0.03844 -0.1176 0.7486 0.0172
-12.750 -0.5408 0.04275 0.03605 -0.1174 0.7413 0.0174
-12.500 -0.5369 0.04083 0.03398 -0.1171 0.7347 0.0176
-12.250 -0.5311 0.03924 0.03228 -0.1167 0.7279 0.0179
-12.000 -0.5247 0.03770 0.03060 -0.1161 0.7221 0.0182
-11.750 -0.5171 0.03625 0.02902 -0.1156 0.7161 0.0186
-11.500 -0.5084 0.03490 0.02752 -0.1149 0.7106 0.0190
-11.250 -0.4989 0.03364 0.02610 -0.1142 0.7058 0.0197
-11.000 -0.4880 0.03244 0.02475 -0.1135 0.7006 0.0205
-10.750 -0.4746 0.03131 0.02343 -0.1127 0.6959 0.0209
-10.500 -0.4607 0.03026 0.02217 -0.1118 0.6919 0.0216
-10.250 -0.4459 0.02915 0.02104 -0.1109 0.6874 0.0220
-10.000 -0.4324 0.02816 0.02001 -0.1100 0.6830 0.0226
-9.750 -0.4190 0.02726 0.01904 -0.1091 0.6789 0.0233
-9.500 -0.4054 0.02641 0.01810 -0.1081 0.6753 0.0240
-9.250 -0.3920 0.02554 0.01718 -0.1071 0.6710 0.0248
-9.000 -0.3794 0.02469 0.01623 -0.1058 0.6670 0.0259
-8.750 -0.3662 0.02398 0.01539 -0.1046 0.6633 0.0270
-8.500 -0.3601 0.02310 0.01447 -0.1026 0.6603 0.0279
-8.250 -0.3511 0.02242 0.01379 -0.1008 0.6568 0.0294
-8.000 -0.3374 0.02179 0.01310 -0.0995 0.6534 0.0311
-7.750 -0.3229 0.02117 0.01239 -0.0983 0.6503 0.0328
-7.500 -0.3084 0.02050 0.01164 -0.0970 0.6476 0.0351
-7.250 -0.2912 0.01995 0.01102 -0.0961 0.6453 0.0382
-7.000 -0.2726 0.01944 0.01047 -0.0953 0.6424 0.0423
-6.750 -0.2534 0.01893 0.00995 -0.0946 0.6395 0.0483
-6.500 -0.2336 0.01842 0.00941 -0.0940 0.6367 0.0559
-6.250 -0.2128 0.01793 0.00893 -0.0935 0.6342 0.0664
-6.000 -0.1917 0.01744 0.00845 -0.0931 0.6318 0.0846
-5.750 -0.1709 0.01687 0.00797 -0.0927 0.6296 0.1154
-5.500 -0.1516 0.01613 0.00750 -0.0923 0.6270 0.1695
-5.250 -0.1319 0.01536 0.00701 -0.0919 0.6243 0.2378
-5.000 -0.1133 0.01445 0.00655 -0.0914 0.6219 0.3411
-4.750 -0.0921 0.01414 0.00677 -0.0906 0.6195 0.4476
-4.500 -0.0644 0.01433 0.00687 -0.0907 0.6173 0.5060
-4.250 -0.0366 0.01448 0.00687 -0.0908 0.6153 0.5274
-4.000 -0.0086 0.01468 0.00698 -0.0908 0.6134 0.5404
-3.750 0.0188 0.01484 0.00710 -0.0907 0.6111 0.5500
-3.500 0.0464 0.01499 0.00714 -0.0908 0.6089 0.5606
-3.250 0.0738 0.01524 0.00738 -0.0906 0.6067 0.5715
-3.000 0.1014 0.01544 0.00753 -0.0906 0.6045 0.5804
-2.750 0.1291 0.01557 0.00757 -0.0906 0.6025 0.5882
-2.500 0.1571 0.01562 0.00752 -0.0908 0.6008 0.5933
-2.250 0.1852 0.01571 0.00756 -0.0909 0.5992 0.5975
-2.000 0.2132 0.01577 0.00754 -0.0912 0.5977 0.6012
-1.750 0.2407 0.01577 0.00749 -0.0915 0.5959 0.6035
-1.500 0.2683 0.01577 0.00741 -0.0918 0.5940 0.6051
-1.250 0.2961 0.01578 0.00734 -0.0922 0.5922 0.6069
-1.000 0.3238 0.01579 0.00732 -0.0925 0.5905 0.6082
-0.750 0.3517 0.01581 0.00731 -0.0928 0.5889 0.6094
-0.500 0.3797 0.01584 0.00730 -0.0931 0.5875 0.6107
-0.250 0.4078 0.01587 0.00728 -0.0934 0.5861 0.6117
0.000 0.4362 0.01591 0.00727 -0.0938 0.5848 0.6128
0.250 0.4647 0.01596 0.00726 -0.0943 0.5836 0.6140
0.500 0.4920 0.01604 0.00734 -0.0945 0.5820 0.6157
0.750 0.5183 0.01614 0.00746 -0.0946 0.5800 0.6175
1.000 0.5449 0.01624 0.00756 -0.0948 0.5782 0.6192
1.250 0.5719 0.01635 0.00767 -0.0950 0.5765 0.6208
1.500 0.5990 0.01645 0.00776 -0.0952 0.5750 0.6220
1.750 0.6264 0.01656 0.00785 -0.0955 0.5735 0.6232
2.000 0.6537 0.01665 0.00797 -0.0958 0.5721 0.6244
2.250 0.6811 0.01676 0.00809 -0.0960 0.5708 0.6258
2.500 0.7089 0.01687 0.00821 -0.0963 0.5696 0.6271
2.750 0.7369 0.01699 0.00834 -0.0967 0.5685 0.6285
3.000 0.7653 0.01713 0.00848 -0.0972 0.5675 0.6297
3.250 0.7896 0.01734 0.00877 -0.0970 0.5658 0.6311
3.500 0.8132 0.01757 0.00909 -0.0967 0.5638 0.6325
3.750 0.8375 0.01779 0.00938 -0.0964 0.5618 0.6340
4.000 0.8623 0.01801 0.00966 -0.0964 0.5601 0.6356
4.250 0.8876 0.01822 0.00993 -0.0963 0.5584 0.6373
4.500 0.9136 0.01839 0.01014 -0.0964 0.5567 0.6391
4.750 0.9403 0.01851 0.01031 -0.0965 0.5551 0.6406
5.000 0.9678 0.01863 0.01049 -0.0968 0.5536 0.6423
5.250 0.9959 0.01878 0.01068 -0.0972 0.5524 0.6442
5.500 1.0213 0.01903 0.01101 -0.0972 0.5510 0.6463
5.750 1.0392 0.01947 0.01162 -0.0961 0.5488 0.6486
6.000 1.0583 0.01986 0.01214 -0.0951 0.5464 0.6512
6.250 1.0794 0.02019 0.01257 -0.0944 0.5441 0.6539
6.500 1.1023 0.02042 0.01290 -0.0940 0.5419 0.6565
6.750 1.1268 0.02059 0.01319 -0.0938 0.5401 0.6591
7.000 1.1536 0.02073 0.01341 -0.0939 0.5385 0.6622
7.250 1.1825 0.02083 0.01358 -0.0945 0.5371 0.6657
7.500 1.1958 0.02131 0.01422 -0.0925 0.5338 0.6696
7.750 1.2055 0.02180 0.01488 -0.0900 0.5296 0.6733
8.000 1.2251 0.02201 0.01522 -0.0890 0.5267 0.6776
8.250 1.2524 0.02196 0.01526 -0.0892 0.5241 0.6828
8.500 1.2893 0.02160 0.01496 -0.0907 0.5214 0.6884
8.750 1.2733 0.02254 0.01612 -0.0841 0.5155 0.6936
9.000 1.2903 0.02237 0.01603 -0.0823 0.5096 0.7003
9.250 1.3063 0.02227 0.01602 -0.0805 0.5034 0.7075
9.500 1.2971 0.02318 0.01709 -0.0756 0.4955 0.7159
9.750 1.3077 0.02346 0.01747 -0.0736 0.4878 0.7250
10.250 1.2800 0.02750 0.02186 -0.0662 0.4684 0.7479
10.500 1.2812 0.02911 0.02360 -0.0646 0.4577 0.7646
10.750 1.2881 0.03043 0.02505 -0.0637 0.4448 0.7860
11.000 1.2871 0.03268 0.02747 -0.0627 0.4287 0.8196
11.250 1.3068 0.03388 0.02882 -0.0645 0.3926 0.9534
11.500 1.3043 0.03502 0.02961 -0.0613 0.3529 1.0000
11.750 1.2895 0.03815 0.03245 -0.0591 0.3168 1.0000
12.000 1.2751 0.04162 0.03574 -0.0573 0.2854 1.0000
12.250 1.2551 0.04574 0.03963 -0.0555 0.2541 1.0000
12.500 1.2419 0.04949 0.04322 -0.0542 0.2243 1.0000
12.750 1.2277 0.05344 0.04701 -0.0531 0.1967 1.0000
13.000 1.2189 0.05702 0.05045 -0.0523 0.1696 1.0000
13.250 1.2083 0.06082 0.05407 -0.0516 0.1432 1.0000
13.500 1.2022 0.06425 0.05738 -0.0511 0.1192 1.0000
13.750 1.1981 0.06754 0.06055 -0.0507 0.0996 1.0000
14.000 1.1939 0.07088 0.06376 -0.0503 0.0788 1.0000
14.250 1.1927 0.07394 0.06674 -0.0501 0.0647 1.0000
14.500 1.1931 0.07687 0.06964 -0.0500 0.0524 1.0000
14.750 1.1926 0.07995 0.07265 -0.0499 0.0430 1.0000
15.000 1.1946 0.08279 0.07551 -0.0499 0.0366 1.0000
15.250 1.1961 0.08571 0.07843 -0.0500 0.0309 1.0000
15.500 1.1984 0.08858 0.08136 -0.0501 0.0271 1.0000
15.750 1.2003 0.09154 0.08435 -0.0503 0.0240 1.0000
16.000 1.2028 0.09447 0.08734 -0.0505 0.0223 1.0000
16.250 1.2022 0.09781 0.09070 -0.0508 0.0203 1.0000
16.500 1.2047 0.10079 0.09379 -0.0512 0.0189 1.0000
16.750 1.2068 0.10385 0.09693 -0.0516 0.0178 1.0000
17.000 1.2079 0.10706 0.10021 -0.0522 0.0168 1.0000
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Polar data table (+)
Polar graphs
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