FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 100,000 Max Cl/Cd: 29.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617a2-il-100000-n5.txt Download as CSV file: xf-fx6617a2-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2701 0.09676 0.09176 -0.0802 0.8432 0.0285
-12.000 -0.3759 0.07056 0.06533 -0.0963 0.8545 0.0252
-11.750 -0.3921 0.06404 0.05846 -0.1022 0.8266 0.0251
-11.500 -0.4066 0.05929 0.05339 -0.1054 0.8042 0.0250
-11.250 -0.4252 0.05507 0.04881 -0.1072 0.7862 0.0251
-10.750 -0.4460 0.04904 0.04229 -0.1078 0.7577 0.0257
-10.500 -0.4501 0.04685 0.03989 -0.1071 0.7463 0.0260
-10.250 -0.4494 0.04528 0.03818 -0.1060 0.7365 0.0267
-10.000 -0.4491 0.04374 0.03643 -0.1044 0.7276 0.0274
-9.750 -0.4473 0.04170 0.03409 -0.1029 0.7203 0.0282
-9.500 -0.4417 0.03958 0.03164 -0.1017 0.7131 0.0289
-9.250 -0.4320 0.03740 0.02906 -0.1005 0.7073 0.0296
-9.000 -0.4191 0.03535 0.02663 -0.0993 0.7007 0.0306
-8.750 -0.4022 0.03360 0.02459 -0.0985 0.6948 0.0317
-8.500 -0.3837 0.03247 0.02339 -0.0980 0.6894 0.0334
-8.250 -0.3646 0.03135 0.02213 -0.0974 0.6836 0.0354
-8.000 -0.3431 0.03015 0.02067 -0.0967 0.6787 0.0373
-7.750 -0.3213 0.02902 0.01935 -0.0961 0.6747 0.0396
-7.500 -0.3008 0.02804 0.01840 -0.0955 0.6698 0.0417
-7.250 -0.2794 0.02714 0.01743 -0.0947 0.6654 0.0437
-7.000 -0.2582 0.02640 0.01654 -0.0939 0.6616 0.0463
-6.750 -0.2385 0.02563 0.01567 -0.0929 0.6577 0.0489
-6.500 -0.2208 0.02488 0.01493 -0.0918 0.6534 0.0512
-6.250 -0.2022 0.02425 0.01423 -0.0906 0.6494 0.0540
-6.000 -0.1829 0.02367 0.01350 -0.0896 0.6461 0.0575
-5.750 -0.1641 0.02304 0.01281 -0.0886 0.6433 0.0629
-5.500 -0.1452 0.02249 0.01226 -0.0876 0.6396 0.0725
-5.250 -0.1272 0.02180 0.01168 -0.0865 0.6362 0.0916
-5.000 -0.1102 0.02097 0.01107 -0.0854 0.6330 0.1421
-4.750 -0.0959 0.01985 0.01041 -0.0842 0.6302 0.2503
-4.500 -0.0815 0.01898 0.01018 -0.0826 0.6277 0.3841
-4.250 -0.0614 0.01934 0.01102 -0.0806 0.6240 0.4962
-4.000 -0.0377 0.01988 0.01147 -0.0795 0.6206 0.5502
-3.750 -0.0133 0.02055 0.01203 -0.0783 0.6178 0.5804
-3.500 0.0122 0.02107 0.01245 -0.0772 0.6153 0.5992
-3.250 0.0380 0.02136 0.01255 -0.0765 0.6130 0.6134
-3.000 0.0638 0.02159 0.01271 -0.0758 0.6102 0.6202
-2.750 0.0877 0.02163 0.01260 -0.0755 0.6068 0.6287
-2.500 0.1131 0.02176 0.01267 -0.0750 0.6038 0.6342
-2.250 0.1384 0.02185 0.01262 -0.0746 0.6011 0.6427
-2.000 0.1645 0.02193 0.01260 -0.0743 0.5989 0.6490
-1.750 0.1914 0.02197 0.01250 -0.0742 0.5970 0.6540
-1.500 0.2160 0.02202 0.01243 -0.0742 0.5942 0.6597
-1.250 0.2397 0.02212 0.01251 -0.0737 0.5910 0.6637
-1.000 0.2645 0.02221 0.01256 -0.0733 0.5881 0.6679
-0.750 0.2901 0.02228 0.01252 -0.0733 0.5856 0.6729
-0.500 0.3165 0.02232 0.01246 -0.0734 0.5835 0.6775
-0.250 0.3435 0.02237 0.01244 -0.0734 0.5816 0.6807
0.000 0.3688 0.02249 0.01250 -0.0732 0.5794 0.6842
0.250 0.3907 0.02271 0.01274 -0.0727 0.5760 0.6881
0.500 0.4146 0.02288 0.01286 -0.0726 0.5730 0.6921
0.750 0.4394 0.02302 0.01299 -0.0723 0.5706 0.6949
1.000 0.4651 0.02315 0.01310 -0.0722 0.5685 0.6980
1.250 0.4920 0.02326 0.01315 -0.0724 0.5667 0.7014
1.500 0.5200 0.02335 0.01317 -0.0727 0.5650 0.7051
1.750 0.5389 0.02377 0.01365 -0.0718 0.5616 0.7088
2.000 0.5592 0.02412 0.01407 -0.0710 0.5583 0.7117
2.250 0.5824 0.02440 0.01438 -0.0707 0.5556 0.7148
2.500 0.6074 0.02463 0.01462 -0.0706 0.5535 0.7184
2.750 0.6341 0.02482 0.01478 -0.0708 0.5516 0.7225
3.000 0.6619 0.02495 0.01489 -0.0711 0.5500 0.7258
3.250 0.6807 0.02541 0.01545 -0.0701 0.5470 0.7292
3.500 0.6938 0.02612 0.01628 -0.0685 0.5430 0.7328
3.750 0.7135 0.02660 0.01681 -0.0677 0.5401 0.7370
4.000 0.7370 0.02691 0.01717 -0.0675 0.5378 0.7410
4.250 0.7638 0.02709 0.01738 -0.0676 0.5359 0.7449
4.500 0.7929 0.02723 0.01752 -0.0681 0.5343 0.7492
4.750 0.7989 0.02836 0.01881 -0.0657 0.5299 0.7539
5.000 0.8063 0.02942 0.02001 -0.0635 0.5256 0.7581
5.250 0.8269 0.02988 0.02054 -0.0630 0.5228 0.7630
5.500 0.8533 0.03011 0.02082 -0.0631 0.5208 0.7688
5.750 0.8821 0.03025 0.02103 -0.0635 0.5193 0.7743
6.250 0.8554 0.03428 0.02537 -0.0548 0.5076 0.7881
6.500 0.8808 0.03451 0.02571 -0.0548 0.5056 0.7953
6.750 0.9111 0.03458 0.02588 -0.0554 0.5042 0.8040
7.000 0.9446 0.03453 0.02594 -0.0564 0.5031 0.8145
7.500 0.8912 0.04164 0.03345 -0.0488 0.4870 0.8577
8.000 0.8840 0.04772 0.03978 -0.0483 0.4725 1.0000
8.500 0.8813 0.05316 0.04529 -0.0470 0.4585 1.0000
9.000 0.8802 0.05848 0.05070 -0.0460 0.4447 1.0000
9.250 0.9076 0.05849 0.05079 -0.0460 0.4435 1.0000
9.750 0.9095 0.06353 0.05594 -0.0450 0.4297 1.0000
10.250 0.9171 0.06800 0.06057 -0.0443 0.4163 1.0000
10.500 0.9446 0.06779 0.06045 -0.0441 0.4146 1.0000
11.000 0.9552 0.07190 0.06472 -0.0435 0.4010 1.0000
11.500 0.9698 0.07552 0.06855 -0.0429 0.3875 1.0000
12.000 0.9880 0.07867 0.07191 -0.0423 0.3738 1.0000
12.500 1.0147 0.08043 0.07390 -0.0416 0.3595 1.0000
12.750 1.0304 0.08048 0.07408 -0.0410 0.3491 1.0000
13.000 1.0592 0.07841 0.07210 -0.0400 0.3376 1.0000
13.250 1.0668 0.07969 0.07346 -0.0397 0.3214 1.0000
13.500 1.0762 0.08109 0.07495 -0.0396 0.3069 1.0000
13.750 1.0826 0.08303 0.07697 -0.0395 0.2901 1.0000
14.000 1.1045 0.08263 0.07658 -0.0390 0.2687 1.0000
14.250 1.1279 0.08179 0.07550 -0.0381 0.2309 1.0000
14.500 1.1328 0.08358 0.07696 -0.0377 0.1930 1.0000
14.750 1.1263 0.08724 0.08038 -0.0378 0.1619 1.0000
15.000 1.1171 0.09146 0.08440 -0.0382 0.1346 1.0000
15.250 1.1078 0.09583 0.08861 -0.0387 0.1107 1.0000
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