FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.19 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66182-il-1000000-n5.txt Download as CSV file: xf-fx66182-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7805 0.09481 0.09235 -0.0569 0.9999 0.0050
-17.500 -0.8234 0.08248 0.07981 -0.0643 0.9996 0.0050
-17.250 -0.8436 0.07366 0.07082 -0.0709 0.9985 0.0049
-17.000 -0.8620 0.06615 0.06315 -0.0760 0.9961 0.0049
-16.750 -0.8765 0.06109 0.05798 -0.0779 0.9912 0.0050
-16.500 -0.8328 0.05282 0.04943 -0.0963 0.9315 0.0050
-16.250 -0.7957 0.04753 0.04339 -0.1094 0.7949 0.0052
-16.000 -0.8018 0.04463 0.04025 -0.1099 0.7589 0.0053
-15.750 -0.8048 0.04203 0.03746 -0.1103 0.7355 0.0052
-15.500 -0.8050 0.03986 0.03512 -0.1105 0.7140 0.0053
-15.250 -0.8071 0.03754 0.03265 -0.1105 0.6967 0.0053
-15.000 -0.8055 0.03560 0.03058 -0.1105 0.6832 0.0053
-14.750 -0.8021 0.03384 0.02871 -0.1103 0.6713 0.0053
-14.500 -0.7992 0.03211 0.02685 -0.1100 0.6605 0.0054
-14.250 -0.7949 0.03050 0.02514 -0.1096 0.6508 0.0055
-14.000 -0.7874 0.02917 0.02371 -0.1091 0.6421 0.0056
-13.750 -0.7789 0.02795 0.02240 -0.1087 0.6340 0.0057
-13.500 -0.7730 0.02654 0.02088 -0.1080 0.6264 0.0058
-13.250 -0.7638 0.02541 0.01966 -0.1074 0.6188 0.0058
-13.000 -0.7550 0.02426 0.01841 -0.1066 0.6132 0.0059
-12.750 -0.7452 0.02318 0.01725 -0.1059 0.6079 0.0059
-12.500 -0.7355 0.02213 0.01613 -0.1051 0.6027 0.0061
-12.250 -0.7267 0.02106 0.01498 -0.1041 0.5983 0.0062
-12.000 -0.7161 0.02015 0.01400 -0.1031 0.5944 0.0063
-11.750 -0.7080 0.01921 0.01300 -0.1017 0.5904 0.0065
-11.500 -0.6994 0.01850 0.01222 -0.0998 0.5864 0.0066
-11.250 -0.6902 0.01799 0.01165 -0.0975 0.5828 0.0068
-11.000 -0.6753 0.01749 0.01110 -0.0960 0.5795 0.0070
-10.750 -0.6581 0.01701 0.01056 -0.0949 0.5758 0.0072
-10.500 -0.6399 0.01654 0.01004 -0.0938 0.5725 0.0075
-10.250 -0.6204 0.01613 0.00956 -0.0930 0.5694 0.0077
-10.000 -0.6001 0.01571 0.00909 -0.0922 0.5668 0.0080
-9.750 -0.5788 0.01531 0.00866 -0.0915 0.5644 0.0084
-9.500 -0.5563 0.01498 0.00830 -0.0910 0.5619 0.0089
-9.250 -0.5331 0.01469 0.00800 -0.0905 0.5593 0.0097
-9.000 -0.5098 0.01439 0.00765 -0.0901 0.5567 0.0103
-8.750 -0.4860 0.01413 0.00736 -0.0897 0.5542 0.0110
-8.500 -0.4613 0.01391 0.00712 -0.0894 0.5518 0.0118
-8.250 -0.4360 0.01370 0.00688 -0.0892 0.5497 0.0128
-8.000 -0.4108 0.01347 0.00662 -0.0890 0.5474 0.0135
-7.750 -0.3857 0.01324 0.00635 -0.0888 0.5451 0.0141
-7.500 -0.3610 0.01296 0.00604 -0.0885 0.5429 0.0146
-7.250 -0.3355 0.01275 0.00580 -0.0883 0.5408 0.0153
-7.000 -0.3098 0.01255 0.00557 -0.0882 0.5387 0.0160
-6.750 -0.2840 0.01236 0.00534 -0.0880 0.5366 0.0167
-6.500 -0.2576 0.01217 0.00512 -0.0880 0.5352 0.0172
-6.250 -0.2310 0.01199 0.00492 -0.0879 0.5336 0.0175
-6.000 -0.2055 0.01169 0.00459 -0.0877 0.5318 0.0181
-5.750 -0.1795 0.01144 0.00431 -0.0876 0.5298 0.0189
-5.500 -0.1531 0.01123 0.00408 -0.0876 0.5277 0.0195
-5.250 -0.1265 0.01106 0.00387 -0.0875 0.5256 0.0202
-5.000 -0.0996 0.01090 0.00367 -0.0875 0.5237 0.0208
-4.750 -0.0727 0.01076 0.00350 -0.0875 0.5218 0.0216
-4.500 -0.0453 0.01062 0.00334 -0.0876 0.5205 0.0219
-4.250 -0.0178 0.01047 0.00317 -0.0877 0.5190 0.0227
-4.000 0.0097 0.01032 0.00302 -0.0877 0.5173 0.0241
-3.750 0.0373 0.01019 0.00288 -0.0878 0.5154 0.0261
-3.500 0.0646 0.01003 0.00274 -0.0879 0.5136 0.0333
-3.250 0.0915 0.00981 0.00259 -0.0880 0.5118 0.0552
-3.000 0.1178 0.00951 0.00243 -0.0880 0.5100 0.0981
-2.750 0.1444 0.00926 0.00230 -0.0880 0.5081 0.1395
-2.500 0.1704 0.00894 0.00215 -0.0881 0.5061 0.2007
-2.250 0.1962 0.00845 0.00197 -0.0882 0.5049 0.2921
-2.000 0.2207 0.00775 0.00176 -0.0881 0.5036 0.4365
-1.750 0.2481 0.00756 0.00176 -0.0883 0.5022 0.5029
-1.500 0.2767 0.00754 0.00179 -0.0885 0.5006 0.5246
-1.250 0.3054 0.00756 0.00181 -0.0888 0.4988 0.5393
-1.000 0.3343 0.00760 0.00183 -0.0891 0.4970 0.5493
-0.750 0.3629 0.00762 0.00185 -0.0893 0.4951 0.5557
-0.500 0.3915 0.00767 0.00186 -0.0895 0.4933 0.5595
-0.250 0.4201 0.00773 0.00188 -0.0898 0.4916 0.5641
0.000 0.4488 0.00775 0.00191 -0.0901 0.4903 0.5686
0.250 0.4777 0.00777 0.00194 -0.0904 0.4891 0.5710
0.500 0.5066 0.00780 0.00196 -0.0907 0.4877 0.5736
0.750 0.5354 0.00783 0.00199 -0.0910 0.4861 0.5760
1.000 0.5641 0.00787 0.00202 -0.0913 0.4843 0.5782
1.250 0.5927 0.00792 0.00204 -0.0916 0.4824 0.5798
1.500 0.6211 0.00796 0.00208 -0.0919 0.4806 0.5816
1.750 0.6493 0.00800 0.00212 -0.0921 0.4788 0.5836
2.000 0.6774 0.00806 0.00218 -0.0923 0.4770 0.5856
2.250 0.7058 0.00810 0.00223 -0.0925 0.4754 0.5874
2.500 0.7344 0.00813 0.00228 -0.0929 0.4735 0.5892
2.750 0.7628 0.00818 0.00234 -0.0931 0.4715 0.5913
3.000 0.7911 0.00823 0.00240 -0.0934 0.4697 0.5932
3.250 0.8193 0.00829 0.00246 -0.0936 0.4679 0.5948
3.500 0.8473 0.00835 0.00253 -0.0939 0.4661 0.5963
3.750 0.8750 0.00841 0.00261 -0.0940 0.4642 0.5983
4.000 0.9024 0.00849 0.00270 -0.0942 0.4621 0.6003
4.250 0.9303 0.00854 0.00279 -0.0944 0.4605 0.6023
4.500 0.9584 0.00860 0.00288 -0.0946 0.4588 0.6042
4.750 0.9863 0.00866 0.00298 -0.0948 0.4569 0.6061
5.000 1.0137 0.00872 0.00306 -0.0950 0.4530 0.6080
5.250 1.0400 0.00883 0.00315 -0.0949 0.4476 0.6098
5.500 1.0675 0.00890 0.00325 -0.0951 0.4431 0.6117
5.750 1.0944 0.00897 0.00336 -0.0951 0.4385 0.6138
6.000 1.1202 0.00909 0.00349 -0.0950 0.4332 0.6160
6.250 1.1471 0.00918 0.00361 -0.0951 0.4291 0.6181
6.500 1.1735 0.00927 0.00375 -0.0951 0.4240 0.6203
6.750 1.1985 0.00943 0.00390 -0.0948 0.4179 0.6225
7.000 1.2242 0.00955 0.00405 -0.0947 0.4097 0.6247
7.250 1.2481 0.00975 0.00423 -0.0942 0.4000 0.6268
7.500 1.2697 0.01003 0.00447 -0.0934 0.3834 0.6288
7.750 1.2857 0.01054 0.00486 -0.0916 0.3540 0.6315
8.000 1.2863 0.01167 0.00567 -0.0873 0.2961 0.6341
8.250 1.2662 0.01318 0.00681 -0.0793 0.2306 0.6367
8.500 1.2443 0.01482 0.00816 -0.0714 0.1758 0.6393
8.750 1.2297 0.01634 0.00951 -0.0655 0.1391 0.6418
9.250 1.2015 0.02027 0.01323 -0.0565 0.0832 0.6470
9.500 1.1910 0.02263 0.01554 -0.0535 0.0621 0.6500
9.750 1.1908 0.02454 0.01745 -0.0518 0.0520 0.6532
10.000 1.1852 0.02697 0.01986 -0.0500 0.0389 0.6563
10.250 1.1859 0.02903 0.02193 -0.0487 0.0326 0.6593
10.500 1.1898 0.03086 0.02381 -0.0476 0.0286 0.6629
10.750 1.1916 0.03290 0.02587 -0.0466 0.0240 0.6670
11.000 1.1885 0.03539 0.02836 -0.0454 0.0153 0.6715
11.500 1.1939 0.03947 0.03255 -0.0437 0.0124 0.6809
11.750 1.1990 0.04139 0.03453 -0.0431 0.0119 0.6867
12.000 1.2039 0.04334 0.03655 -0.0425 0.0114 0.6922
12.250 1.2089 0.04535 0.03862 -0.0420 0.0110 0.6992
12.750 1.2180 0.04954 0.04296 -0.0412 0.0101 0.7164
13.000 1.2213 0.05181 0.04532 -0.0409 0.0096 0.7287
13.250 1.2281 0.05374 0.04736 -0.0406 0.0094 0.7471
13.500 1.2338 0.05567 0.04947 -0.0403 0.0092 0.7905
13.750 1.2481 0.05771 0.05197 -0.0420 0.0090 1.0000
14.000 1.2549 0.05977 0.05407 -0.0419 0.0085 1.0000
14.250 1.2600 0.06210 0.05644 -0.0419 0.0082 1.0000
14.500 1.2661 0.06431 0.05869 -0.0419 0.0079 1.0000
14.750 1.2704 0.06675 0.06117 -0.0419 0.0076 1.0000
15.000 1.2746 0.06924 0.06371 -0.0420 0.0074 1.0000
15.250 1.2792 0.07170 0.06622 -0.0422 0.0071 1.0000
15.500 1.2842 0.07418 0.06875 -0.0424 0.0070 1.0000
15.750 1.2910 0.07646 0.07108 -0.0426 0.0068 1.0000
16.000 1.2972 0.07880 0.07347 -0.0429 0.0066 1.0000
16.250 1.3027 0.08127 0.07599 -0.0433 0.0063 1.0000
16.500 1.3082 0.08375 0.07851 -0.0436 0.0061 1.0000
16.750 1.3134 0.08630 0.08110 -0.0441 0.0058 1.0000
17.000 1.3177 0.08900 0.08385 -0.0446 0.0055 1.0000
17.250 1.3223 0.09166 0.08655 -0.0451 0.0053 1.0000
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