FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 200,000 Max Cl/Cd: 67.37 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617a2-il-200000-n5.txt Download as CSV file: xf-fx6617a2-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3138 0.09250 0.08831 -0.0859 0.7978 0.0158
-13.250 -0.3520 0.07867 0.07435 -0.0944 0.7914 0.0155
-13.000 -0.3781 0.06950 0.06497 -0.1011 0.7758 0.0152
-12.750 -0.4088 0.06154 0.05671 -0.1066 0.7616 0.0152
-12.500 -0.4289 0.05635 0.05126 -0.1094 0.7460 0.0151
-12.250 -0.4487 0.05185 0.04649 -0.1110 0.7329 0.0152
-12.000 -0.4652 0.04804 0.04239 -0.1118 0.7210 0.0152
-11.750 -0.4802 0.04456 0.03861 -0.1119 0.7103 0.0153
-11.500 -0.4900 0.04168 0.03545 -0.1115 0.7009 0.0154
-11.250 -0.4990 0.03899 0.03243 -0.1106 0.6925 0.0156
-11.000 -0.5057 0.03661 0.02971 -0.1093 0.6846 0.0159
-10.750 -0.5067 0.03461 0.02744 -0.1077 0.6773 0.0161
-10.500 -0.5006 0.03306 0.02575 -0.1064 0.6705 0.0163
-10.250 -0.4936 0.03182 0.02438 -0.1047 0.6639 0.0167
-10.000 -0.4857 0.03077 0.02318 -0.1029 0.6583 0.0171
-9.750 -0.4743 0.02959 0.02184 -0.1015 0.6525 0.0176
-9.500 -0.4603 0.02844 0.02051 -0.1003 0.6473 0.0183
-9.250 -0.4446 0.02732 0.01916 -0.0991 0.6430 0.0191
-9.000 -0.4281 0.02643 0.01802 -0.0980 0.6384 0.0202
-8.750 -0.4109 0.02532 0.01692 -0.0971 0.6341 0.0212
-8.500 -0.3931 0.02459 0.01611 -0.0962 0.6303 0.0223
-8.250 -0.3745 0.02384 0.01524 -0.0952 0.6269 0.0236
-8.000 -0.3552 0.02307 0.01434 -0.0943 0.6228 0.0247
-7.750 -0.3371 0.02225 0.01345 -0.0932 0.6189 0.0258
-7.500 -0.3185 0.02164 0.01281 -0.0923 0.6155 0.0273
-7.250 -0.2987 0.02111 0.01219 -0.0915 0.6124 0.0290
-7.000 -0.2777 0.02062 0.01160 -0.0907 0.6093 0.0308
-6.750 -0.2590 0.01993 0.01089 -0.0898 0.6062 0.0323
-6.500 -0.2390 0.01936 0.01027 -0.0889 0.6032 0.0336
-6.250 -0.2178 0.01890 0.00973 -0.0882 0.6005 0.0355
-6.000 -0.1959 0.01848 0.00920 -0.0876 0.5980 0.0375
-5.750 -0.1737 0.01806 0.00867 -0.0869 0.5956 0.0391
-5.500 -0.1520 0.01756 0.00814 -0.0863 0.5926 0.0417
-5.250 -0.1289 0.01718 0.00771 -0.0858 0.5896 0.0454
-5.000 -0.1059 0.01678 0.00728 -0.0852 0.5869 0.0525
-4.750 -0.0832 0.01633 0.00687 -0.0847 0.5845 0.0721
-4.500 -0.0621 0.01572 0.00646 -0.0841 0.5824 0.1237
-4.000 -0.0221 0.01431 0.00570 -0.0827 0.5782 0.2995
-3.750 -0.0033 0.01368 0.00560 -0.0815 0.5758 0.4221
-3.500 0.0206 0.01369 0.00586 -0.0807 0.5733 0.5011
-3.250 0.0472 0.01386 0.00598 -0.0804 0.5708 0.5353
-3.000 0.0743 0.01403 0.00608 -0.0801 0.5685 0.5545
-2.750 0.1013 0.01429 0.00627 -0.0798 0.5665 0.5742
-2.250 0.1555 0.01466 0.00645 -0.0794 0.5626 0.5975
-2.000 0.1828 0.01472 0.00651 -0.0793 0.5602 0.6015
-1.750 0.2100 0.01479 0.00652 -0.0793 0.5577 0.6064
-1.500 0.2374 0.01484 0.00646 -0.0793 0.5554 0.6118
-1.250 0.2649 0.01490 0.00646 -0.0793 0.5534 0.6160
-1.000 0.2925 0.01497 0.00649 -0.0794 0.5516 0.6201
-0.750 0.3204 0.01504 0.00646 -0.0795 0.5500 0.6240
-0.500 0.3479 0.01511 0.00644 -0.0796 0.5481 0.6278
-0.250 0.3746 0.01515 0.00648 -0.0796 0.5456 0.6305
0.000 0.4016 0.01519 0.00653 -0.0796 0.5433 0.6329
0.250 0.4287 0.01525 0.00657 -0.0796 0.5411 0.6355
0.500 0.4561 0.01532 0.00660 -0.0797 0.5392 0.6382
0.750 0.4836 0.01539 0.00663 -0.0799 0.5374 0.6413
1.000 0.5113 0.01547 0.00664 -0.0801 0.5357 0.6447
1.250 0.5392 0.01554 0.00668 -0.0803 0.5341 0.6471
1.500 0.5657 0.01564 0.00680 -0.0802 0.5321 0.6496
1.750 0.5916 0.01574 0.00696 -0.0801 0.5297 0.6526
2.000 0.6179 0.01585 0.00709 -0.0800 0.5275 0.6559
2.250 0.6446 0.01596 0.00720 -0.0801 0.5255 0.6589
2.500 0.6715 0.01607 0.00730 -0.0801 0.5236 0.6614
2.750 0.6985 0.01615 0.00742 -0.0802 0.5219 0.6635
3.000 0.7259 0.01624 0.00751 -0.0803 0.5201 0.6660
3.250 0.7536 0.01635 0.00760 -0.0805 0.5185 0.6689
3.500 0.7788 0.01651 0.00784 -0.0803 0.5163 0.6717
3.750 0.8035 0.01668 0.00808 -0.0801 0.5140 0.6745
4.000 0.8288 0.01684 0.00829 -0.0799 0.5117 0.6772
4.250 0.8543 0.01696 0.00850 -0.0797 0.5094 0.6797
4.500 0.8804 0.01708 0.00867 -0.0797 0.5074 0.6827
4.750 0.9071 0.01720 0.00882 -0.0797 0.5056 0.6859
5.000 0.9343 0.01733 0.00897 -0.0799 0.5040 0.6892
5.250 0.9603 0.01751 0.00919 -0.0798 0.5020 0.6924
5.500 0.9820 0.01774 0.00959 -0.0791 0.4993 0.6952
5.750 1.0052 0.01797 0.00993 -0.0786 0.4969 0.6983
6.000 1.0294 0.01818 0.01025 -0.0783 0.4947 0.7021
6.250 1.0545 0.01837 0.01051 -0.0781 0.4927 0.7064
6.500 1.0803 0.01852 0.01074 -0.0780 0.4908 0.7102
6.750 1.1069 0.01865 0.01095 -0.0781 0.4890 0.7142
7.000 1.1326 0.01883 0.01122 -0.0780 0.4872 0.7187
7.250 1.1508 0.01922 0.01178 -0.0768 0.4842 0.7235
7.500 1.1708 0.01953 0.01227 -0.0758 0.4816 0.7280
7.750 1.1924 0.01971 0.01258 -0.0750 0.4786 0.7336
8.000 1.2173 0.01974 0.01269 -0.0747 0.4756 0.7400
8.250 1.2423 0.01969 0.01273 -0.0744 0.4716 0.7469
8.750 1.2787 0.01979 0.01312 -0.0716 0.4600 0.7647
9.000 1.2954 0.01993 0.01342 -0.0700 0.4544 0.7763
9.250 1.3092 0.02003 0.01369 -0.0678 0.4473 0.7923
9.750 1.3495 0.02003 0.01418 -0.0666 0.4240 0.9315
10.000 1.3478 0.02047 0.01461 -0.0622 0.4091 1.0000
10.250 1.3487 0.02119 0.01532 -0.0588 0.3911 1.0000
10.500 1.3465 0.02228 0.01632 -0.0556 0.3707 1.0000
10.750 1.3459 0.02366 0.01770 -0.0531 0.3539 1.0000
11.000 1.3400 0.02557 0.01957 -0.0506 0.3325 1.0000
11.250 1.3285 0.02816 0.02207 -0.0483 0.3096 1.0000
11.500 1.3111 0.03151 0.02531 -0.0461 0.2811 1.0000
11.750 1.2921 0.03524 0.02893 -0.0443 0.2571 1.0000
12.000 1.2708 0.03936 0.03293 -0.0427 0.2329 1.0000
12.250 1.2489 0.04366 0.03712 -0.0413 0.2084 1.0000
12.500 1.2319 0.04771 0.04108 -0.0403 0.1861 1.0000
12.750 1.2109 0.05234 0.04555 -0.0394 0.1589 1.0000
13.000 1.1994 0.05615 0.04928 -0.0388 0.1392 1.0000
13.250 1.1857 0.06031 0.05330 -0.0384 0.1151 1.0000
13.500 1.1770 0.06404 0.05693 -0.0381 0.0958 1.0000
13.750 1.1683 0.06782 0.06061 -0.0379 0.0769 1.0000
14.000 1.1629 0.07133 0.06404 -0.0378 0.0615 1.0000
14.250 1.1594 0.07469 0.06735 -0.0378 0.0493 1.0000
14.500 1.1581 0.07783 0.07048 -0.0379 0.0409 1.0000
14.750 1.1564 0.08107 0.07371 -0.0380 0.0340 1.0000
15.000 1.1562 0.08419 0.07683 -0.0382 0.0290 1.0000
15.250 1.1572 0.08721 0.07990 -0.0384 0.0247 1.0000
15.750 1.1604 0.09317 0.08599 -0.0390 0.0207 1.0000
16.000 1.1626 0.09612 0.08900 -0.0394 0.0192 1.0000
16.250 1.1630 0.09932 0.09224 -0.0399 0.0179 1.0000
16.500 1.1640 0.10249 0.09548 -0.0404 0.0171 1.0000
16.750 1.1656 0.10561 0.09869 -0.0410 0.0163 1.0000
17.000 1.1666 0.10880 0.10196 -0.0417 0.0155 1.0000
17.250 1.1673 0.11207 0.10530 -0.0424 0.0150 1.0000
17.500 1.1666 0.11558 0.10887 -0.0433 0.0145 1.0000
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