FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 200,000 Max Cl/Cd: 65.03 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617a2-il-200000.txt Download as CSV file: xf-fx6617a2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1511 0.08964 0.08554 -0.0896 0.7380 0.0721
-11.500 -0.1311 0.08818 0.08402 -0.0878 0.7289 0.0735
-11.250 -0.2173 0.08371 0.07955 -0.1029 0.7583 0.0727
-11.000 -0.1957 0.08360 0.07934 -0.1004 0.7462 0.0743
-10.750 -0.1923 0.08053 0.07619 -0.1012 0.7382 0.0762
-10.500 -0.2023 0.07511 0.07078 -0.1044 0.7314 0.0780
-10.250 -0.2371 0.06701 0.06264 -0.1104 0.7267 0.0791
-10.000 -0.2689 0.06174 0.05727 -0.1134 0.7218 0.0797
-9.750 -0.3011 0.05773 0.05317 -0.1144 0.7158 0.0803
-9.500 -0.4246 0.04311 0.03705 -0.1065 0.7147 0.0383
-9.250 -0.4206 0.03911 0.03282 -0.1053 0.7097 0.0370
-9.000 -0.4158 0.03597 0.02932 -0.1036 0.7048 0.0361
-8.750 -0.4060 0.03322 0.02621 -0.1019 0.6993 0.0356
-8.500 -0.3915 0.03094 0.02357 -0.1006 0.6944 0.0357
-8.250 -0.3734 0.02906 0.02135 -0.0995 0.6902 0.0364
-8.000 -0.3541 0.02785 0.01986 -0.0984 0.6851 0.0380
-7.750 -0.3327 0.02594 0.01776 -0.0978 0.6808 0.0402
-7.500 -0.3094 0.02481 0.01656 -0.0975 0.6771 0.0424
-7.250 -0.2857 0.02384 0.01549 -0.0969 0.6735 0.0445
-7.000 -0.2625 0.02316 0.01470 -0.0963 0.6694 0.0470
-6.750 -0.2400 0.02199 0.01348 -0.0956 0.6656 0.0499
-6.500 -0.2180 0.02131 0.01280 -0.0950 0.6621 0.0532
-6.250 -0.1956 0.02072 0.01212 -0.0942 0.6590 0.0558
-6.000 -0.1743 0.02017 0.01154 -0.0933 0.6552 0.0581
-5.750 -0.1561 0.01936 0.01076 -0.0921 0.6518 0.0616
-5.500 -0.1358 0.01879 0.01017 -0.0912 0.6487 0.0655
-5.250 -0.1138 0.01834 0.00961 -0.0904 0.6460 0.0708
-5.000 -0.0937 0.01771 0.00895 -0.0895 0.6436 0.0843
-4.500 -0.0776 0.01481 0.00809 -0.0847 0.6376 0.4666
-4.250 -0.0525 0.01517 0.00848 -0.0838 0.6343 0.5310
-4.000 -0.0256 0.01557 0.00877 -0.0832 0.6315 0.5569
-3.750 0.0017 0.01601 0.00908 -0.0828 0.6292 0.5759
-3.500 0.0283 0.01658 0.00958 -0.0822 0.6268 0.5942
-3.250 0.0539 0.01709 0.01012 -0.0813 0.6238 0.6090
-3.000 0.0799 0.01751 0.01054 -0.0806 0.6207 0.6210
-2.750 0.1060 0.01802 0.01103 -0.0796 0.6179 0.6356
-2.500 0.1323 0.01839 0.01136 -0.0789 0.6154 0.6484
-2.250 0.1596 0.01863 0.01151 -0.0786 0.6134 0.6563
-2.000 0.1861 0.01869 0.01144 -0.0787 0.6113 0.6620
-1.750 0.2109 0.01878 0.01157 -0.0782 0.6084 0.6658
-1.500 0.2364 0.01890 0.01166 -0.0779 0.6054 0.6716
-1.250 0.2622 0.01896 0.01164 -0.0778 0.6027 0.6783
-1.000 0.2888 0.01905 0.01171 -0.0775 0.6004 0.6830
-0.750 0.3162 0.01912 0.01169 -0.0776 0.5984 0.6880
-0.500 0.3440 0.01922 0.01165 -0.0781 0.5966 0.6927
-0.250 0.3678 0.01935 0.01183 -0.0776 0.5942 0.6956
0.000 0.3918 0.01949 0.01201 -0.0773 0.5913 0.6990
0.250 0.4174 0.01959 0.01209 -0.0772 0.5885 0.7028
0.500 0.4440 0.01967 0.01210 -0.0774 0.5860 0.7068
0.750 0.4711 0.01972 0.01211 -0.0776 0.5840 0.7098
1.000 0.4987 0.01982 0.01218 -0.0777 0.5822 0.7128
1.250 0.5265 0.02003 0.01233 -0.0780 0.5805 0.7165
1.500 0.5470 0.02035 0.01274 -0.0772 0.5776 0.7203
1.750 0.5700 0.02062 0.01303 -0.0769 0.5745 0.7240
2.000 0.5946 0.02075 0.01320 -0.0766 0.5718 0.7271
2.250 0.6207 0.02089 0.01336 -0.0766 0.5696 0.7304
2.500 0.6480 0.02104 0.01348 -0.0768 0.5677 0.7338
2.750 0.6767 0.02118 0.01356 -0.0773 0.5660 0.7373
3.000 0.7008 0.02152 0.01393 -0.0772 0.5637 0.7406
3.250 0.7169 0.02202 0.01460 -0.0757 0.5599 0.7436
3.500 0.7387 0.02239 0.01503 -0.0752 0.5570 0.7467
3.750 0.7642 0.02260 0.01527 -0.0752 0.5546 0.7502
4.000 0.7920 0.02274 0.01538 -0.0755 0.5526 0.7542
4.250 0.8204 0.02282 0.01548 -0.0758 0.5508 0.7576
4.500 0.8495 0.02304 0.01571 -0.0763 0.5493 0.7611
4.750 0.8542 0.02414 0.01703 -0.0734 0.5449 0.7650
5.000 0.8702 0.02483 0.01782 -0.0722 0.5415 0.7691
5.250 0.8937 0.02512 0.01817 -0.0719 0.5390 0.7732
5.500 0.9219 0.02521 0.01832 -0.0722 0.5372 0.7777
5.750 0.9515 0.02527 0.01841 -0.0727 0.5355 0.7829
6.000 0.9819 0.02544 0.01859 -0.0735 0.5340 0.7877
6.250 0.9614 0.02772 0.02119 -0.0674 0.5273 0.7929
6.500 0.9754 0.02849 0.02207 -0.0659 0.5242 0.7991
6.750 1.0025 0.02865 0.02231 -0.0661 0.5222 0.8053
7.000 1.0344 0.02857 0.02229 -0.0669 0.5208 0.8129
7.250 1.0678 0.02846 0.02226 -0.0679 0.5194 0.8213
7.500 1.1022 0.02854 0.02240 -0.0692 0.5182 0.8310
7.750 0.9413 0.03782 0.03208 -0.0486 0.4988 0.8528
8.000 1.0007 0.03633 0.03076 -0.0523 0.4991 0.8771
8.250 1.0869 0.03479 0.02949 -0.0614 0.4993 0.9536
8.500 1.1789 0.03136 0.02606 -0.0687 0.5004 1.0000
8.750 1.0980 0.03709 0.03185 -0.0575 0.4904 1.0000
9.000 1.1013 0.03852 0.03332 -0.0557 0.4853 1.0000
9.250 1.1613 0.03536 0.03021 -0.0577 0.4818 1.0000
9.500 1.3317 0.02654 0.02131 -0.0730 0.4793 1.0000
9.750 1.3833 0.02372 0.01837 -0.0751 0.4693 1.0000
10.000 1.4133 0.02225 0.01683 -0.0746 0.4588 1.0000
10.250 1.4099 0.02274 0.01748 -0.0699 0.4514 1.0000
10.500 1.4346 0.02206 0.01679 -0.0689 0.4434 1.0000
10.750 1.4237 0.02294 0.01785 -0.0634 0.4358 1.0000
11.000 1.4294 0.02310 0.01805 -0.0603 0.4251 1.0000
11.250 1.4327 0.02360 0.01858 -0.0574 0.4134 1.0000
11.500 1.4271 0.02486 0.01992 -0.0541 0.4000 1.0000
11.750 1.4209 0.02654 0.02167 -0.0514 0.3858 1.0000
12.000 1.4111 0.02882 0.02397 -0.0491 0.3675 1.0000
12.250 1.3976 0.03166 0.02676 -0.0470 0.3429 1.0000
12.500 1.3809 0.03499 0.02996 -0.0451 0.3141 1.0000
12.750 1.3566 0.03917 0.03396 -0.0432 0.2798 1.0000
13.000 1.3319 0.04358 0.03818 -0.0415 0.2519 1.0000
13.250 1.3050 0.04846 0.04288 -0.0402 0.2228 1.0000
13.500 1.2802 0.05342 0.04766 -0.0392 0.1948 1.0000
13.750 1.2567 0.05847 0.05254 -0.0385 0.1660 1.0000
14.000 1.2311 0.06396 0.05780 -0.0380 0.1331 1.0000
14.250 1.2077 0.06938 0.06297 -0.0377 0.1018 1.0000
14.500 1.1890 0.07445 0.06783 -0.0377 0.0764 1.0000
14.750 1.1732 0.07930 0.07251 -0.0376 0.0576 1.0000
15.000 1.1630 0.08363 0.07678 -0.0377 0.0478 1.0000
15.250 1.1544 0.08785 0.08099 -0.0380 0.0421 1.0000
15.500 1.1526 0.09126 0.08446 -0.0382 0.0386 1.0000
15.750 1.1471 0.09513 0.08833 -0.0385 0.0361 1.0000
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