WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 500,000 Max Cl/Cd: 105.55 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617ai-il-500000-n5.txt Download as CSV file: xf-fx6617ai-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6639 0.10493 0.10158 -0.0411 0.7695 0.0102
-16.000 -0.7037 0.09244 0.08887 -0.0483 0.7654 0.0102
-15.750 -0.7302 0.08323 0.07941 -0.0538 0.7503 0.0102
-15.500 -0.7501 0.07579 0.07173 -0.0584 0.7330 0.0102
-15.250 -0.7654 0.06950 0.06520 -0.0622 0.7160 0.0103
-15.000 -0.7790 0.06389 0.05936 -0.0655 0.7009 0.0103
-14.750 -0.7909 0.05891 0.05418 -0.0682 0.6876 0.0104
-14.500 -0.7993 0.05477 0.04985 -0.0702 0.6756 0.0105
-14.250 -0.8038 0.05123 0.04615 -0.0719 0.6649 0.0106
-14.000 -0.8052 0.04820 0.04298 -0.0732 0.6551 0.0107
-13.750 -0.8039 0.04553 0.04017 -0.0744 0.6461 0.0108
-13.500 -0.8005 0.04317 0.03769 -0.0754 0.6382 0.0109
-13.250 -0.7955 0.04100 0.03541 -0.0762 0.6309 0.0111
-13.000 -0.7893 0.03901 0.03330 -0.0770 0.6245 0.0112
-12.750 -0.7818 0.03713 0.03131 -0.0776 0.6190 0.0114
-12.500 -0.7734 0.03537 0.02943 -0.0781 0.6136 0.0116
-12.000 -0.7535 0.03213 0.02593 -0.0789 0.6046 0.0121
-11.750 -0.7420 0.03062 0.02430 -0.0792 0.6003 0.0123
-11.500 -0.7294 0.02921 0.02274 -0.0794 0.5962 0.0125
-11.250 -0.7156 0.02788 0.02127 -0.0796 0.5924 0.0128
-11.000 -0.7006 0.02664 0.01991 -0.0799 0.5887 0.0130
-10.750 -0.6861 0.02555 0.01870 -0.0798 0.5849 0.0131
-10.500 -0.6705 0.02463 0.01765 -0.0796 0.5813 0.0133
-10.250 -0.6521 0.02378 0.01666 -0.0794 0.5780 0.0135
-10.000 -0.6356 0.02263 0.01544 -0.0791 0.5754 0.0138
-9.750 -0.6163 0.02175 0.01450 -0.0789 0.5726 0.0140
-9.500 -0.5953 0.02103 0.01372 -0.0788 0.5697 0.0143
-9.250 -0.5733 0.02041 0.01304 -0.0788 0.5669 0.0146
-9.000 -0.5505 0.01985 0.01241 -0.0787 0.5643 0.0150
-8.750 -0.5274 0.01932 0.01180 -0.0787 0.5617 0.0154
-8.500 -0.5038 0.01876 0.01119 -0.0787 0.5593 0.0159
-8.250 -0.4797 0.01824 0.01060 -0.0787 0.5567 0.0164
-8.000 -0.4554 0.01773 0.01002 -0.0787 0.5540 0.0168
-7.750 -0.4310 0.01722 0.00943 -0.0787 0.5515 0.0171
-7.500 -0.4067 0.01668 0.00881 -0.0786 0.5492 0.0174
-7.250 -0.3827 0.01608 0.00816 -0.0786 0.5471 0.0179
-7.000 -0.3574 0.01564 0.00766 -0.0787 0.5452 0.0185
-6.750 -0.3313 0.01524 0.00723 -0.0788 0.5432 0.0192
-6.500 -0.3049 0.01488 0.00683 -0.0790 0.5412 0.0199
-6.250 -0.2782 0.01455 0.00645 -0.0791 0.5390 0.0208
-6.000 -0.2512 0.01426 0.00610 -0.0793 0.5368 0.0217
-5.750 -0.2246 0.01392 0.00572 -0.0795 0.5346 0.0232
-5.500 -0.1975 0.01366 0.00542 -0.0796 0.5325 0.0251
-5.250 -0.1702 0.01345 0.00514 -0.0798 0.5305 0.0274
-5.000 -0.1427 0.01318 0.00487 -0.0801 0.5289 0.0312
-4.750 -0.1150 0.01294 0.00462 -0.0803 0.5271 0.0367
-4.500 -0.0875 0.01265 0.00437 -0.0806 0.5253 0.0472
-4.250 -0.0607 0.01224 0.00409 -0.0809 0.5235 0.0803
-4.000 -0.0342 0.01178 0.00381 -0.0811 0.5216 0.1302
-3.750 -0.0083 0.01119 0.00351 -0.0814 0.5198 0.2080
-3.500 0.0173 0.01056 0.00320 -0.0817 0.5180 0.2986
-3.250 0.0429 0.01000 0.00299 -0.0819 0.5162 0.4081
-3.000 0.0707 0.00984 0.00294 -0.0822 0.5145 0.4565
-2.750 0.0992 0.00974 0.00292 -0.0825 0.5129 0.4865
-2.500 0.1278 0.00970 0.00294 -0.0827 0.5113 0.5112
-2.250 0.1568 0.00972 0.00297 -0.0830 0.5096 0.5331
-2.000 0.1858 0.00973 0.00298 -0.0833 0.5080 0.5425
-1.750 0.2151 0.00977 0.00295 -0.0837 0.5063 0.5493
-1.500 0.2441 0.00979 0.00296 -0.0840 0.5047 0.5561
-1.250 0.2733 0.00984 0.00296 -0.0844 0.5030 0.5638
-1.000 0.3022 0.00989 0.00297 -0.0847 0.5013 0.5696
-0.750 0.3311 0.00996 0.00299 -0.0851 0.4996 0.5749
-0.500 0.3605 0.00999 0.00299 -0.0855 0.4982 0.5791
-0.250 0.3897 0.01002 0.00301 -0.0859 0.4968 0.5828
0.000 0.4188 0.01005 0.00305 -0.0863 0.4953 0.5865
0.250 0.4479 0.01009 0.00309 -0.0867 0.4937 0.5903
0.500 0.4771 0.01014 0.00311 -0.0871 0.4922 0.5941
0.750 0.5062 0.01019 0.00314 -0.0875 0.4906 0.5975
1.000 0.5350 0.01023 0.00318 -0.0878 0.4890 0.6007
1.250 0.5638 0.01029 0.00323 -0.0882 0.4874 0.6043
1.500 0.5927 0.01037 0.00328 -0.0885 0.4858 0.6080
1.750 0.6215 0.01046 0.00334 -0.0889 0.4844 0.6114
2.000 0.6505 0.01051 0.00342 -0.0893 0.4832 0.6144
2.250 0.6793 0.01056 0.00351 -0.0897 0.4818 0.6174
2.500 0.7081 0.01062 0.00360 -0.0901 0.4803 0.6209
2.750 0.7369 0.01069 0.00369 -0.0905 0.4787 0.6244
3.000 0.7656 0.01077 0.00377 -0.0909 0.4770 0.6277
3.250 0.7942 0.01083 0.00386 -0.0912 0.4754 0.6305
3.500 0.8226 0.01091 0.00396 -0.0915 0.4739 0.6335
3.750 0.8510 0.01099 0.00407 -0.0919 0.4725 0.6369
4.000 0.8794 0.01110 0.00418 -0.0922 0.4712 0.6404
4.250 0.9078 0.01122 0.00430 -0.0926 0.4697 0.6437
4.500 0.9361 0.01130 0.00444 -0.0929 0.4683 0.6465
4.750 0.9643 0.01138 0.00459 -0.0932 0.4667 0.6497
5.000 0.9925 0.01147 0.00475 -0.0935 0.4650 0.6532
5.250 1.0206 0.01157 0.00490 -0.0939 0.4635 0.6568
5.500 1.0487 0.01168 0.00505 -0.0942 0.4619 0.6602
5.750 1.0765 0.01177 0.00521 -0.0944 0.4602 0.6635
6.000 1.1042 0.01188 0.00537 -0.0947 0.4585 0.6671
6.250 1.1319 0.01200 0.00553 -0.0949 0.4570 0.6710
6.500 1.1595 0.01215 0.00571 -0.0952 0.4554 0.6751
6.750 1.1867 0.01225 0.00591 -0.0954 0.4530 0.6789
7.000 1.2137 0.01232 0.00609 -0.0955 0.4494 0.6831
7.250 1.2404 0.01240 0.00623 -0.0956 0.4452 0.6875
7.500 1.2665 0.01251 0.00635 -0.0956 0.4408 0.6921
7.750 1.2925 0.01256 0.00652 -0.0956 0.4330 0.6964
8.000 1.3172 0.01269 0.00666 -0.0953 0.4256 0.7010
8.250 1.3431 0.01281 0.00689 -0.0953 0.4181 0.7061
8.500 1.3673 0.01299 0.00710 -0.0950 0.4103 0.7112
8.750 1.3911 0.01318 0.00736 -0.0947 0.3992 0.7168
9.000 1.4137 0.01346 0.00767 -0.0942 0.3862 0.7226
9.250 1.4316 0.01393 0.00810 -0.0930 0.3637 0.7283
9.500 1.4365 0.01504 0.00902 -0.0900 0.3198 0.7351
9.750 1.4256 0.01677 0.01051 -0.0848 0.2726 0.7426
10.000 1.4021 0.01958 0.01310 -0.0793 0.2214 0.7514
10.250 1.3707 0.02386 0.01719 -0.0754 0.1731 0.7607
10.500 1.3422 0.02901 0.02224 -0.0736 0.1366 0.7709
10.750 1.3153 0.03429 0.02747 -0.0723 0.1051 0.7821
11.000 1.2950 0.03885 0.03202 -0.0710 0.0826 0.7958
11.250 1.2807 0.04273 0.03593 -0.0698 0.0666 0.8170
11.500 1.2687 0.04577 0.03924 -0.0681 0.0561 0.9963
11.750 1.2633 0.04890 0.04237 -0.0673 0.0484 1.0002
12.000 1.2605 0.05188 0.04536 -0.0667 0.0426 1.0002
12.250 1.2590 0.05480 0.04830 -0.0662 0.0377 1.0002
12.500 1.2605 0.05744 0.05097 -0.0659 0.0339 1.0002
12.750 1.2610 0.06022 0.05377 -0.0655 0.0306 1.0002
13.000 1.2633 0.06284 0.05642 -0.0653 0.0278 1.0002
13.250 1.2654 0.06551 0.05913 -0.0650 0.0253 1.0002
13.500 1.2671 0.06824 0.06189 -0.0648 0.0231 1.0002
13.750 1.2705 0.07078 0.06447 -0.0646 0.0213 1.0002
14.000 1.2729 0.07350 0.06721 -0.0645 0.0198 1.0002
14.250 1.2754 0.07620 0.06993 -0.0644 0.0183 1.0002
14.500 1.2791 0.07879 0.07259 -0.0643 0.0173 1.0002
14.750 1.2825 0.08142 0.07525 -0.0643 0.0163 1.0002
15.000 1.2853 0.08411 0.07798 -0.0643 0.0152 1.0002
15.250 1.2870 0.08699 0.08091 -0.0643 0.0144 1.0002
15.500 1.2917 0.08950 0.08349 -0.0644 0.0135 1.0002
15.750 1.2956 0.09212 0.08616 -0.0645 0.0128 1.0002
16.000 1.2982 0.09493 0.08901 -0.0646 0.0121 1.0002
16.250 1.3007 0.09773 0.09185 -0.0648 0.0114 1.0002
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