WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 200,000 Max Cl/Cd: 68.84 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617ai-il-200000-n5.txt Download as CSV file: xf-fx6617ai-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5574 0.07502 0.07030 -0.0671 0.7171 0.0175
-13.000 -0.5856 0.06727 0.06226 -0.0723 0.7092 0.0174
-12.750 -0.6044 0.06164 0.05637 -0.0758 0.7002 0.0174
-12.500 -0.6180 0.05704 0.05153 -0.0783 0.6910 0.0175
-12.250 -0.6278 0.05313 0.04740 -0.0801 0.6825 0.0176
-12.000 -0.6337 0.04981 0.04386 -0.0815 0.6743 0.0177
-11.750 -0.6366 0.04690 0.04075 -0.0825 0.6669 0.0179
-11.500 -0.6368 0.04432 0.03796 -0.0832 0.6599 0.0180
-11.250 -0.6345 0.04199 0.03542 -0.0838 0.6538 0.0183
-11.000 -0.6294 0.03996 0.03319 -0.0842 0.6477 0.0186
-10.750 -0.6233 0.03826 0.03129 -0.0842 0.6425 0.0190
-10.500 -0.6152 0.03674 0.02956 -0.0838 0.6379 0.0195
-10.250 -0.6035 0.03512 0.02772 -0.0835 0.6331 0.0201
-10.000 -0.5897 0.03352 0.02585 -0.0831 0.6287 0.0206
-9.750 -0.5737 0.03201 0.02404 -0.0827 0.6248 0.0211
-9.500 -0.5552 0.03058 0.02238 -0.0823 0.6205 0.0215
-9.250 -0.5355 0.02942 0.02096 -0.0820 0.6162 0.0219
-9.000 -0.5154 0.02807 0.01957 -0.0817 0.6123 0.0226
-8.750 -0.4944 0.02716 0.01857 -0.0815 0.6090 0.0233
-8.500 -0.4726 0.02626 0.01759 -0.0813 0.6056 0.0240
-8.250 -0.4504 0.02533 0.01658 -0.0810 0.6021 0.0245
-8.000 -0.4283 0.02445 0.01561 -0.0807 0.5990 0.0251
-7.750 -0.4061 0.02363 0.01467 -0.0804 0.5961 0.0258
-7.500 -0.3839 0.02289 0.01380 -0.0800 0.5935 0.0265
-7.250 -0.3612 0.02218 0.01300 -0.0798 0.5906 0.0273
-7.000 -0.3392 0.02139 0.01217 -0.0796 0.5874 0.0281
-6.750 -0.3170 0.02064 0.01139 -0.0794 0.5844 0.0292
-6.500 -0.2935 0.02005 0.01073 -0.0794 0.5816 0.0307
-6.250 -0.2692 0.01955 0.01013 -0.0793 0.5791 0.0328
-6.000 -0.2446 0.01908 0.00953 -0.0793 0.5770 0.0351
-5.750 -0.2202 0.01848 0.00891 -0.0794 0.5746 0.0383
-5.500 -0.1946 0.01804 0.00840 -0.0795 0.5720 0.0421
-5.250 -0.1694 0.01753 0.00788 -0.0796 0.5696 0.0487
-5.000 -0.1440 0.01703 0.00742 -0.0797 0.5672 0.0648
-4.750 -0.1199 0.01631 0.00691 -0.0799 0.5649 0.1148
-4.500 -0.0968 0.01541 0.00639 -0.0802 0.5628 0.2098
-4.250 -0.0742 0.01448 0.00597 -0.0803 0.5608 0.3329
-4.000 -0.0494 0.01406 0.00596 -0.0802 0.5584 0.4362
-3.750 -0.0224 0.01403 0.00604 -0.0802 0.5561 0.4864
-3.500 0.0054 0.01411 0.00614 -0.0802 0.5539 0.5173
-3.250 0.0333 0.01428 0.00630 -0.0801 0.5518 0.5420
-3.000 0.0615 0.01447 0.00642 -0.0801 0.5499 0.5614
-2.750 0.0899 0.01459 0.00645 -0.0802 0.5481 0.5712
-2.500 0.1188 0.01465 0.00637 -0.0806 0.5463 0.5782
-2.250 0.1473 0.01473 0.00639 -0.0808 0.5443 0.5846
-2.000 0.1756 0.01482 0.00645 -0.0810 0.5420 0.5928
-1.750 0.2040 0.01490 0.00647 -0.0812 0.5398 0.5996
-1.500 0.2325 0.01496 0.00650 -0.0814 0.5379 0.6042
-1.250 0.2612 0.01501 0.00647 -0.0818 0.5360 0.6091
-1.000 0.2901 0.01505 0.00642 -0.0822 0.5343 0.6138
-0.750 0.3186 0.01511 0.00644 -0.0825 0.5327 0.6173
-0.500 0.3473 0.01518 0.00645 -0.0828 0.5312 0.6215
-0.250 0.3761 0.01526 0.00646 -0.0832 0.5295 0.6259
0.000 0.4044 0.01533 0.00652 -0.0835 0.5274 0.6301
0.250 0.4324 0.01541 0.00663 -0.0838 0.5253 0.6336
0.500 0.4606 0.01550 0.00672 -0.0840 0.5234 0.6377
0.750 0.4891 0.01560 0.00678 -0.0844 0.5217 0.6420
1.000 0.5177 0.01569 0.00684 -0.0848 0.5200 0.6460
1.250 0.5459 0.01578 0.00694 -0.0851 0.5185 0.6494
1.500 0.5743 0.01587 0.00701 -0.0854 0.5170 0.6534
1.750 0.6030 0.01598 0.00707 -0.0858 0.5155 0.6577
2.000 0.6313 0.01611 0.00720 -0.0861 0.5138 0.6617
2.250 0.6584 0.01624 0.00742 -0.0863 0.5118 0.6649
2.500 0.6859 0.01640 0.00763 -0.0865 0.5099 0.6689
2.750 0.7136 0.01655 0.00782 -0.0868 0.5081 0.6733
3.000 0.7416 0.01671 0.00799 -0.0871 0.5064 0.6775
3.250 0.7692 0.01683 0.00816 -0.0874 0.5047 0.6807
3.500 0.7971 0.01695 0.00831 -0.0876 0.5031 0.6847
3.750 0.8253 0.01708 0.00845 -0.0880 0.5016 0.6892
4.000 0.8538 0.01723 0.00859 -0.0884 0.5003 0.6935
4.250 0.8809 0.01742 0.00886 -0.0885 0.4989 0.6970
4.500 0.9068 0.01767 0.00923 -0.0886 0.4969 0.7013
4.750 0.9331 0.01791 0.00957 -0.0887 0.4948 0.7060
5.000 0.9595 0.01812 0.00986 -0.0888 0.4927 0.7103
5.250 0.9860 0.01830 0.01014 -0.0889 0.4908 0.7145
5.500 1.0131 0.01849 0.01040 -0.0891 0.4892 0.7194
5.750 1.0405 0.01869 0.01064 -0.0894 0.4877 0.7247
6.000 1.0678 0.01884 0.01088 -0.0896 0.4863 0.7291
6.250 1.0958 0.01900 0.01109 -0.0899 0.4850 0.7343
6.500 1.1203 0.01934 0.01156 -0.0898 0.4828 0.7401
6.750 1.1436 0.01970 0.01211 -0.0895 0.4805 0.7450
7.000 1.1678 0.02002 0.01257 -0.0894 0.4783 0.7509
7.250 1.1927 0.02029 0.01296 -0.0893 0.4761 0.7569
7.500 1.2181 0.02049 0.01328 -0.0892 0.4742 0.7630
7.750 1.2445 0.02069 0.01358 -0.0894 0.4725 0.7703
8.000 1.2713 0.02083 0.01382 -0.0894 0.4710 0.7772
8.250 1.2944 0.02106 0.01419 -0.0891 0.4677 0.7853
8.500 1.3137 0.02124 0.01460 -0.0881 0.4621 0.7944
8.750 1.3423 0.02064 0.01399 -0.0880 0.4557 0.8054
9.000 1.3582 0.02080 0.01439 -0.0865 0.4476 0.8194
9.250 1.3818 0.02053 0.01422 -0.0857 0.4413 0.8383
9.500 1.3963 0.02075 0.01473 -0.0839 0.4338 0.8793
9.750 1.4187 0.02061 0.01471 -0.0833 0.4262 1.0002
10.000 1.4316 0.02114 0.01539 -0.0816 0.4167 1.0002
10.250 1.4420 0.02155 0.01587 -0.0794 0.4051 1.0002
10.500 1.4491 0.02221 0.01657 -0.0771 0.3896 1.0002
10.750 1.4511 0.02323 0.01754 -0.0745 0.3680 1.0002
11.000 1.4430 0.02519 0.01939 -0.0718 0.3370 1.0002
11.250 1.4221 0.02871 0.02273 -0.0693 0.3021 1.0002
11.500 1.3945 0.03349 0.02735 -0.0675 0.2715 1.0002
11.750 1.3650 0.03879 0.03253 -0.0661 0.2430 1.0002
12.000 1.3328 0.04443 0.03803 -0.0646 0.2131 1.0002
12.250 1.2998 0.05021 0.04364 -0.0633 0.1829 1.0002
12.500 1.2715 0.05576 0.04903 -0.0623 0.1546 1.0002
12.750 1.2494 0.06088 0.05400 -0.0616 0.1269 1.0002
13.000 1.2293 0.06593 0.05888 -0.0611 0.0981 1.0002
13.250 1.2145 0.07051 0.06332 -0.0608 0.0759 1.0002
13.500 1.2062 0.07444 0.06717 -0.0606 0.0614 1.0002
13.750 1.2018 0.07798 0.07070 -0.0605 0.0526 1.0002
14.000 1.1988 0.08137 0.07409 -0.0604 0.0464 1.0002
14.250 1.1994 0.08441 0.07718 -0.0604 0.0420 1.0002
14.500 1.1988 0.08762 0.08041 -0.0605 0.0383 1.0002
14.750 1.1990 0.09076 0.08361 -0.0606 0.0356 1.0002
15.000 1.2011 0.09367 0.08659 -0.0607 0.0330 1.0002
15.250 1.2012 0.09683 0.08980 -0.0610 0.0308 1.0002
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