FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 500,000 Max Cl/Cd: 107.32 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66182-il-500000.txt Download as CSV file: xf-fx66182-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.1528 0.11681 0.11338 -0.0697 0.6780 0.0235
-13.500 -0.1493 0.11351 0.11006 -0.0713 0.6722 0.0242
-13.250 -0.4479 0.05806 0.05469 -0.1114 0.8467 0.0139
-12.500 -0.5068 0.04631 0.04193 -0.1140 0.7387 0.0139
-12.250 -0.5200 0.04331 0.03868 -0.1139 0.7217 0.0139
-12.000 -0.5310 0.04053 0.03567 -0.1135 0.7078 0.0139
-11.750 -0.5431 0.03766 0.03255 -0.1126 0.6963 0.0139
-11.500 -0.5498 0.03502 0.02970 -0.1115 0.6866 0.0141
-11.000 -0.5502 0.03131 0.02566 -0.1085 0.6701 0.0144
-10.750 -0.5461 0.03017 0.02439 -0.1065 0.6631 0.0147
-10.500 -0.5414 0.02882 0.02289 -0.1043 0.6569 0.0148
-10.250 -0.5297 0.02783 0.02179 -0.1030 0.6507 0.0151
-10.000 -0.5176 0.02658 0.02034 -0.1016 0.6455 0.0154
-9.750 -0.5029 0.02538 0.01898 -0.1004 0.6405 0.0159
-9.500 -0.4867 0.02426 0.01768 -0.0993 0.6359 0.0164
-9.250 -0.4693 0.02331 0.01652 -0.0982 0.6317 0.0170
-9.000 -0.4502 0.02260 0.01564 -0.0973 0.6278 0.0174
-8.750 -0.4313 0.02082 0.01378 -0.0965 0.6240 0.0183
-8.500 -0.4115 0.02005 0.01298 -0.0958 0.6203 0.0191
-8.250 -0.3909 0.01951 0.01236 -0.0951 0.6169 0.0203
-8.000 -0.3696 0.01893 0.01168 -0.0943 0.6136 0.0215
-7.750 -0.3515 0.01791 0.01063 -0.0933 0.6104 0.0233
-7.500 -0.3305 0.01735 0.01005 -0.0926 0.6070 0.0247
-7.250 -0.3085 0.01689 0.00952 -0.0919 0.6039 0.0262
-7.000 -0.2849 0.01658 0.00910 -0.0915 0.6011 0.0273
-6.750 -0.2670 0.01572 0.00820 -0.0904 0.5984 0.0289
-6.500 -0.2442 0.01527 0.00774 -0.0899 0.5959 0.0302
-6.250 -0.2201 0.01492 0.00736 -0.0895 0.5933 0.0318
-6.000 -0.1950 0.01467 0.00705 -0.0893 0.5907 0.0334
-5.750 -0.1725 0.01415 0.00649 -0.0887 0.5883 0.0356
-5.500 -0.1481 0.01381 0.00609 -0.0884 0.5858 0.0375
-5.250 -0.1228 0.01357 0.00576 -0.0882 0.5831 0.0391
-5.000 -0.0971 0.01328 0.00544 -0.0880 0.5810 0.0408
-4.750 -0.0715 0.01297 0.00510 -0.0878 0.5786 0.0440
-4.500 -0.0459 0.01265 0.00480 -0.0877 0.5764 0.0528
-4.250 -0.0247 0.01177 0.00434 -0.0872 0.5743 0.1471
-4.000 -0.0045 0.01071 0.00386 -0.0868 0.5722 0.2977
-3.750 0.0171 0.00991 0.00361 -0.0864 0.5701 0.4514
-3.500 0.0445 0.00993 0.00371 -0.0864 0.5677 0.5069
-3.250 0.0727 0.00998 0.00375 -0.0865 0.5658 0.5331
-3.000 0.1012 0.01005 0.00380 -0.0866 0.5637 0.5478
-2.750 0.1297 0.01015 0.00388 -0.0868 0.5616 0.5604
-2.500 0.1581 0.01029 0.00398 -0.0868 0.5595 0.5725
-2.250 0.1866 0.01046 0.00411 -0.0869 0.5573 0.5846
-2.000 0.2151 0.01070 0.00427 -0.0870 0.5553 0.5963
-1.750 0.2437 0.01085 0.00442 -0.0871 0.5533 0.6031
-1.500 0.2724 0.01103 0.00454 -0.0873 0.5515 0.6097
-1.250 0.3006 0.01107 0.00458 -0.0875 0.5498 0.6148
-1.000 0.3289 0.01115 0.00469 -0.0876 0.5479 0.6198
-0.750 0.3574 0.01121 0.00471 -0.0878 0.5459 0.6240
-0.500 0.3862 0.01124 0.00469 -0.0881 0.5438 0.6268
-0.250 0.4148 0.01124 0.00465 -0.0885 0.5418 0.6292
0.000 0.4435 0.01126 0.00465 -0.0888 0.5401 0.6315
0.250 0.4723 0.01134 0.00470 -0.0891 0.5384 0.6339
0.500 0.5013 0.01149 0.00481 -0.0895 0.5365 0.6367
0.750 0.5294 0.01152 0.00485 -0.0897 0.5350 0.6392
1.000 0.5577 0.01156 0.00489 -0.0900 0.5332 0.6418
1.250 0.5860 0.01160 0.00491 -0.0903 0.5312 0.6441
1.500 0.6142 0.01159 0.00493 -0.0905 0.5292 0.6461
1.750 0.6425 0.01162 0.00497 -0.0908 0.5272 0.6482
2.000 0.6711 0.01168 0.00502 -0.0911 0.5255 0.6506
2.250 0.6998 0.01176 0.00508 -0.0915 0.5239 0.6530
2.500 0.7288 0.01191 0.00520 -0.0920 0.5220 0.6553
2.750 0.7566 0.01201 0.00532 -0.0922 0.5202 0.6578
3.000 0.7840 0.01203 0.00539 -0.0924 0.5182 0.6601
3.250 0.8115 0.01205 0.00547 -0.0925 0.5160 0.6623
3.500 0.8392 0.01210 0.00556 -0.0927 0.5140 0.6645
3.750 0.8672 0.01216 0.00564 -0.0930 0.5121 0.6669
4.000 0.8955 0.01224 0.00573 -0.0933 0.5104 0.6696
4.250 0.9240 0.01235 0.00584 -0.0937 0.5087 0.6724
4.500 0.9529 0.01254 0.00600 -0.0941 0.5068 0.6748
4.750 0.9797 0.01261 0.00616 -0.0942 0.5049 0.6772
5.000 1.0060 0.01267 0.00632 -0.0942 0.5028 0.6797
5.250 1.0328 0.01275 0.00647 -0.0943 0.5008 0.6823
5.500 1.0600 0.01284 0.00662 -0.0944 0.4987 0.6855
5.750 1.0875 0.01289 0.00670 -0.0946 0.4963 0.6887
6.000 1.1154 0.01291 0.00672 -0.0948 0.4936 0.6917
6.250 1.1428 0.01303 0.00687 -0.0950 0.4906 0.6946
6.500 1.1668 0.01300 0.00698 -0.0945 0.4872 0.6978
6.750 1.1919 0.01295 0.00699 -0.0942 0.4830 0.7013
7.000 1.2182 0.01292 0.00699 -0.0941 0.4793 0.7050
7.250 1.2454 0.01302 0.00710 -0.0943 0.4760 0.7086
7.500 1.2682 0.01302 0.00727 -0.0936 0.4724 0.7127
7.750 1.2917 0.01297 0.00731 -0.0930 0.4673 0.7175
8.000 1.3166 0.01298 0.00732 -0.0927 0.4626 0.7223
8.250 1.3374 0.01295 0.00743 -0.0916 0.4560 0.7272
8.500 1.3571 0.01288 0.00739 -0.0902 0.4461 0.7330
8.750 1.3749 0.01289 0.00746 -0.0886 0.4336 0.7392
9.000 1.3930 0.01298 0.00765 -0.0871 0.4211 0.7464
9.250 1.4113 0.01315 0.00789 -0.0857 0.4105 0.7550
9.500 1.4243 0.01336 0.00817 -0.0833 0.3967 0.7663
9.750 1.4320 0.01370 0.00855 -0.0799 0.3799 0.7825
10.000 1.4315 0.01427 0.00917 -0.0754 0.3559 0.8140
10.250 1.4283 0.01504 0.01009 -0.0709 0.3257 1.0000
10.500 1.4148 0.01662 0.01151 -0.0656 0.2930 1.0000
10.750 1.3919 0.01904 0.01376 -0.0603 0.2593 1.0000
11.000 1.3697 0.02204 0.01664 -0.0562 0.2312 1.0000
11.250 1.3484 0.02550 0.02001 -0.0532 0.2056 1.0000
11.500 1.3251 0.02946 0.02387 -0.0507 0.1801 1.0000
11.750 1.3057 0.03330 0.02764 -0.0487 0.1589 1.0000
12.000 1.2833 0.03750 0.03174 -0.0469 0.1346 1.0000
12.250 1.2661 0.04136 0.03551 -0.0454 0.1145 1.0000
12.500 1.2495 0.04534 0.03940 -0.0442 0.0936 1.0000
12.750 1.2368 0.04910 0.04307 -0.0434 0.0743 1.0000
13.000 1.2237 0.05304 0.04691 -0.0427 0.0553 1.0000
13.250 1.2170 0.05645 0.05027 -0.0422 0.0421 1.0000
13.500 1.2110 0.05987 0.05363 -0.0419 0.0321 1.0000
13.750 1.2100 0.06286 0.05663 -0.0418 0.0262 1.0000
14.000 1.2121 0.06554 0.05933 -0.0417 0.0227 1.0000
14.250 1.2130 0.06841 0.06221 -0.0417 0.0201 1.0000
14.500 1.2164 0.07104 0.06489 -0.0418 0.0189 1.0000
14.750 1.2190 0.07381 0.06771 -0.0419 0.0177 1.0000
15.000 1.2204 0.07675 0.07068 -0.0421 0.0168 1.0000
15.250 1.2195 0.08002 0.07401 -0.0424 0.0158 1.0000
15.500 1.2212 0.08302 0.07708 -0.0427 0.0154 1.0000
15.750 1.2237 0.08595 0.08009 -0.0431 0.0146 1.0000
16.000 1.2244 0.08918 0.08339 -0.0436 0.0142 1.0000
16.250 1.2248 0.09244 0.08671 -0.0441 0.0135 1.0000
16.500 1.2232 0.09604 0.09037 -0.0448 0.0131 1.0000
16.750 1.2187 0.10004 0.09442 -0.0455 0.0126 1.0000
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Polar data table (+)
Polar graphs
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