FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.76 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617a2-il-1000000-n5.txt Download as CSV file: xf-fx6617a2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-17AII-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
------ -------- --------- --------- -------- -------- --------
-18.000 -0.6957 0.11323 0.11099 -0.0485 0.9996 0.0051
-17.750 -0.7651 0.09691 0.09445 -0.0562 0.9999 0.0050
-17.500 -0.8006 0.08549 0.08284 -0.0633 0.9995 0.0051
-17.250 -0.8209 0.07657 0.07375 -0.0698 0.9984 0.0051
-17.000 -0.8511 0.06758 0.06458 -0.0752 0.9959 0.0050
-16.750 -0.8659 0.06350 0.06043 -0.0751 0.9623 0.0051
-16.500 -0.7951 0.05341 0.04993 -0.1017 0.9189 0.0051
-16.250 -0.7645 0.04854 0.04436 -0.1129 0.7953 0.0052
-16.000 -0.7727 0.04527 0.04085 -0.1137 0.7603 0.0051
-15.750 -0.7804 0.04219 0.03758 -0.1143 0.7357 0.0051
-15.500 -0.7783 0.04021 0.03545 -0.1144 0.7151 0.0052
-15.250 -0.7814 0.03785 0.03291 -0.1144 0.6955 0.0052
-15.000 -0.7832 0.03566 0.03059 -0.1143 0.6821 0.0053
-14.750 -0.7833 0.03368 0.02849 -0.1141 0.6703 0.0054
-14.500 -0.7806 0.03199 0.02668 -0.1136 0.6588 0.0055
-14.250 -0.7808 0.03010 0.02468 -0.1130 0.6498 0.0056
-14.000 -0.7751 0.02871 0.02319 -0.1124 0.6413 0.0056
-13.750 -0.7693 0.02736 0.02175 -0.1117 0.6336 0.0057
-13.500 -0.7617 0.02616 0.02047 -0.1109 0.6263 0.0058
-13.250 -0.7539 0.02499 0.01922 -0.1101 0.6196 0.0059
-13.000 -0.7461 0.02386 0.01800 -0.1091 0.6129 0.0059
-12.750 -0.7372 0.02280 0.01687 -0.1082 0.6074 0.0061
-12.500 -0.7277 0.02182 0.01582 -0.1072 0.6024 0.0062
-12.250 -0.7178 0.02091 0.01484 -0.1061 0.5975 0.0063
-12.000 -0.7090 0.01999 0.01384 -0.1049 0.5937 0.0064
-11.750 -0.7003 0.01918 0.01297 -0.1033 0.5898 0.0065
-11.500 -0.6929 0.01847 0.01219 -0.1011 0.5861 0.0066
-11.250 -0.6846 0.01796 0.01161 -0.0986 0.5824 0.0067
-11.000 -0.6714 0.01747 0.01105 -0.0968 0.5794 0.0069
-10.750 -0.6551 0.01697 0.01049 -0.0955 0.5765 0.0070
-10.500 -0.6373 0.01652 0.00998 -0.0943 0.5730 0.0072
-10.250 -0.6189 0.01607 0.00948 -0.0932 0.5698 0.0076
-10.000 -0.5991 0.01567 0.00904 -0.0923 0.5665 0.0079
-9.750 -0.5780 0.01532 0.00866 -0.0915 0.5639 0.0084
-9.500 -0.5561 0.01498 0.00829 -0.0909 0.5616 0.0090
-9.250 -0.5338 0.01465 0.00793 -0.0903 0.5592 0.0095
-9.000 -0.5099 0.01441 0.00770 -0.0899 0.5566 0.0105
-8.750 -0.4858 0.01419 0.00744 -0.0895 0.5542 0.0114
-8.500 -0.4617 0.01396 0.00716 -0.0891 0.5517 0.0122
-8.000 -0.4132 0.01348 0.00663 -0.0883 0.5476 0.0135
-7.750 -0.3880 0.01327 0.00640 -0.0881 0.5457 0.0142
-7.500 -0.3628 0.01306 0.00616 -0.0878 0.5433 0.0150
-7.250 -0.3377 0.01284 0.00590 -0.0875 0.5411 0.0155
-7.000 -0.3124 0.01264 0.00565 -0.0873 0.5387 0.0158
-6.750 -0.2873 0.01241 0.00538 -0.0870 0.5367 0.0163
-6.500 -0.2631 0.01211 0.00504 -0.0866 0.5347 0.0169
-6.250 -0.2379 0.01187 0.00478 -0.0863 0.5329 0.0175
-6.000 -0.2120 0.01166 0.00454 -0.0861 0.5315 0.0181
-5.750 -0.1859 0.01146 0.00432 -0.0860 0.5299 0.0187
-5.500 -0.1597 0.01128 0.00412 -0.0858 0.5282 0.0194
-5.250 -0.1332 0.01112 0.00393 -0.0857 0.5262 0.0200
-5.000 -0.1071 0.01093 0.00371 -0.0855 0.5242 0.0211
-4.750 -0.0808 0.01076 0.00350 -0.0854 0.5222 0.0218
-4.500 -0.0544 0.01061 0.00333 -0.0852 0.5203 0.0225
-4.250 -0.0278 0.01049 0.00318 -0.0851 0.5184 0.0231
-4.000 -0.0008 0.01035 0.00303 -0.0851 0.5171 0.0240
-3.750 0.0264 0.01023 0.00290 -0.0851 0.5156 0.0252
-3.500 0.0534 0.01009 0.00277 -0.0851 0.5138 0.0293
-3.250 0.0796 0.00988 0.00262 -0.0849 0.5120 0.0484
-3.000 0.1053 0.00963 0.00248 -0.0847 0.5103 0.0801
-2.750 0.1306 0.00934 0.00233 -0.0845 0.5086 0.1249
-2.500 0.1557 0.00906 0.00220 -0.0842 0.5067 0.1748
-2.250 0.1799 0.00870 0.00205 -0.0838 0.5049 0.2505
-2.000 0.2039 0.00834 0.00190 -0.0834 0.5029 0.3194
-1.750 0.2253 0.00770 0.00173 -0.0826 0.5018 0.4578
-1.500 0.2522 0.00759 0.00174 -0.0825 0.5005 0.5012
-1.250 0.2802 0.00757 0.00176 -0.0826 0.4991 0.5202
-1.000 0.3085 0.00759 0.00178 -0.0828 0.4975 0.5340
-0.750 0.3366 0.00760 0.00179 -0.0829 0.4959 0.5412
-0.500 0.3650 0.00763 0.00180 -0.0831 0.4941 0.5464
-0.250 0.3932 0.00767 0.00181 -0.0833 0.4922 0.5508
0.000 0.4211 0.00770 0.00185 -0.0833 0.4904 0.5584
0.250 0.4491 0.00776 0.00187 -0.0835 0.4886 0.5621
0.500 0.4774 0.00781 0.00190 -0.0837 0.4872 0.5650
0.750 0.5056 0.00782 0.00193 -0.0839 0.4860 0.5679
1.000 0.5339 0.00785 0.00196 -0.0840 0.4846 0.5703
1.250 0.5621 0.00788 0.00200 -0.0842 0.4830 0.5725
1.500 0.5903 0.00791 0.00203 -0.0844 0.4813 0.5748
1.750 0.6183 0.00796 0.00207 -0.0846 0.4794 0.5773
2.000 0.6462 0.00801 0.00211 -0.0847 0.4775 0.5799
2.250 0.6738 0.00807 0.00216 -0.0848 0.4756 0.5819
2.500 0.7010 0.00812 0.00221 -0.0848 0.4734 0.5841
2.750 0.7288 0.00816 0.00228 -0.0850 0.4717 0.5862
3.000 0.7567 0.00820 0.00234 -0.0851 0.4699 0.5882
3.250 0.7845 0.00824 0.00240 -0.0853 0.4681 0.5901
3.500 0.8122 0.00830 0.00247 -0.0854 0.4664 0.5920
3.750 0.8397 0.00836 0.00254 -0.0855 0.4646 0.5940
4.000 0.8670 0.00842 0.00262 -0.0856 0.4628 0.5960
4.500 0.9206 0.00857 0.00279 -0.0856 0.4591 0.5995
4.750 0.9475 0.00864 0.00289 -0.0856 0.4572 0.6014
5.000 0.9748 0.00867 0.00297 -0.0857 0.4533 0.6034
5.250 1.0009 0.00875 0.00305 -0.0855 0.4476 0.6054
5.500 1.0262 0.00886 0.00316 -0.0853 0.4433 0.6077
5.750 1.0532 0.00892 0.00327 -0.0853 0.4411 0.6100
6.000 1.0798 0.00900 0.00338 -0.0853 0.4382 0.6120
6.250 1.1051 0.00910 0.00350 -0.0850 0.4322 0.6140
6.500 1.1297 0.00921 0.00363 -0.0846 0.4267 0.6163
6.750 1.1553 0.00930 0.00377 -0.0844 0.4218 0.6193
7.000 1.1794 0.00943 0.00391 -0.0840 0.4160 0.6217
7.250 1.2035 0.00957 0.00408 -0.0835 0.4094 0.6248
7.500 1.2247 0.00980 0.00427 -0.0825 0.3958 0.6278
7.750 1.2434 0.01010 0.00452 -0.0811 0.3781 0.6306
8.000 1.2540 0.01066 0.00494 -0.0783 0.3462 0.6334
8.250 1.2454 0.01163 0.00565 -0.0719 0.2976 0.6360
8.500 1.2219 0.01314 0.00682 -0.0632 0.2372 0.6388
8.750 1.2052 0.01453 0.00800 -0.0563 0.1954 0.6416
9.000 1.1807 0.01641 0.00966 -0.0491 0.1521 0.6441
9.250 1.1644 0.01835 0.01149 -0.0441 0.1216 0.6466
9.500 1.1508 0.02059 0.01365 -0.0403 0.0961 0.6496
9.750 1.1482 0.02247 0.01552 -0.0380 0.0818 0.6529
10.000 1.1360 0.02522 0.01820 -0.0355 0.0601 0.6559
10.250 1.1373 0.02714 0.02012 -0.0341 0.0521 0.6592
10.500 1.1296 0.02981 0.02276 -0.0323 0.0373 0.6624
10.750 1.1332 0.03166 0.02464 -0.0313 0.0329 0.6665
11.000 1.1353 0.03366 0.02666 -0.0303 0.0286 0.6709
11.250 1.1314 0.03616 0.02916 -0.0291 0.0171 0.6753
11.500 1.1311 0.03845 0.03147 -0.0281 0.0134 0.6799
11.750 1.1371 0.04025 0.03333 -0.0276 0.0130 0.6858
12.000 1.1424 0.04214 0.03527 -0.0270 0.0123 0.6918
12.250 1.1467 0.04419 0.03739 -0.0266 0.0114 0.6985
12.750 1.1601 0.04797 0.04132 -0.0259 0.0103 0.7161
13.000 1.1680 0.04979 0.04323 -0.0258 0.0102 0.7290
13.250 1.1746 0.05184 0.04539 -0.0257 0.0100 0.7480
13.500 1.1848 0.05374 0.04748 -0.0263 0.0096 0.7910
13.750 1.2829 0.05956 0.05382 -0.0496 0.0084 0.9440
14.000 1.2874 0.06181 0.05611 -0.0489 0.0082 0.9998
14.250 1.2959 0.06399 0.05834 -0.0492 0.0080 1.0000
14.500 1.3015 0.06625 0.06064 -0.0492 0.0077 1.0000
14.750 1.3078 0.06841 0.06284 -0.0491 0.0074 1.0000
15.000 1.3122 0.07080 0.06528 -0.0490 0.0071 1.0000
15.250 1.3158 0.07331 0.06783 -0.0489 0.0070 1.0000
15.500 1.3211 0.07562 0.07019 -0.0489 0.0068 1.0000
15.750 1.3242 0.07823 0.07284 -0.0490 0.0065 1.0000
16.000 1.3274 0.08082 0.07546 -0.0490 0.0061 1.0000
16.250 1.3318 0.08327 0.07797 -0.0491 0.0060 1.0000
16.500 1.3351 0.08591 0.08066 -0.0492 0.0059 1.0000
16.750 1.3408 0.08822 0.08302 -0.0494 0.0055 1.0000
17.000 1.3445 0.09082 0.08567 -0.0496 0.0053 1.0000
17.250 1.3471 0.09358 0.08849 -0.0498 0.0052 1.0000
17.500 1.3513 0.09609 0.09104 -0.0500 0.0050 1.0000
17.750 1.3547 0.09875 0.09374 -0.0504 0.0048 1.0000
18.000 1.3566 0.10159 0.09662 -0.0507 0.0046 1.0000
18.250 1.3588 0.10443 0.09950 -0.0511 0.0044 1.0000
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