WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| 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: 62.93 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617ai-il-200000.txt Download as CSV file: xf-fx6617ai-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3569 0.12031 0.11633 -0.0534 0.7419 0.0638
-12.250 -0.3386 0.11794 0.11383 -0.0493 0.7297 0.0653
-12.000 -0.3246 0.11629 0.11207 -0.0482 0.7203 0.0667
-11.750 -0.3162 0.11359 0.10933 -0.0487 0.7123 0.0687
-11.500 -0.3146 0.10974 0.10543 -0.0505 0.7065 0.0715
-11.250 -0.3830 0.09317 0.08898 -0.0695 0.7092 0.0761
-11.000 -0.3615 0.09134 0.08711 -0.0650 0.7021 0.0780
-10.750 -0.3385 0.09211 0.08782 -0.0614 0.6943 0.0795
-10.500 -0.2403 0.08006 0.07583 -0.0694 0.6766 0.0926
-10.250 -0.2292 0.07811 0.07382 -0.0686 0.6729 0.0949
-10.000 -0.2397 0.07242 0.06814 -0.0712 0.6706 0.0978
-9.750 -0.2948 0.05988 0.05562 -0.0798 0.6712 0.0991
-9.500 -0.5288 0.04408 0.03773 -0.0875 0.6844 0.0422
-9.250 -0.5186 0.04036 0.03373 -0.0873 0.6797 0.0416
-9.000 -0.5052 0.03785 0.03085 -0.0869 0.6754 0.0418
-8.750 -0.4885 0.03555 0.02817 -0.0865 0.6717 0.0420
-8.500 -0.4691 0.03311 0.02547 -0.0862 0.6673 0.0418
-8.250 -0.4477 0.03103 0.02312 -0.0859 0.6630 0.0418
-8.000 -0.4249 0.02968 0.02146 -0.0856 0.6590 0.0423
-7.750 -0.4014 0.02829 0.01979 -0.0853 0.6554 0.0431
-7.500 -0.3764 0.02632 0.01774 -0.0851 0.6513 0.0437
-7.250 -0.3513 0.02487 0.01624 -0.0849 0.6475 0.0443
-7.000 -0.3266 0.02378 0.01511 -0.0845 0.6442 0.0454
-6.750 -0.3023 0.02293 0.01419 -0.0842 0.6413 0.0467
-6.500 -0.2783 0.02216 0.01341 -0.0839 0.6382 0.0484
-6.250 -0.2545 0.02145 0.01268 -0.0835 0.6349 0.0505
-6.000 -0.2306 0.02080 0.01197 -0.0832 0.6316 0.0529
-5.750 -0.2091 0.01988 0.01107 -0.0830 0.6286 0.0576
-5.500 -0.1845 0.01938 0.01046 -0.0829 0.6258 0.0634
-5.250 -0.1614 0.01862 0.00971 -0.0828 0.6231 0.0742
-5.000 -0.1415 0.01720 0.00879 -0.0827 0.6202 0.1471
-4.750 -0.1276 0.01528 0.00826 -0.0823 0.6175 0.4308
-4.500 -0.1014 0.01538 0.00849 -0.0819 0.6148 0.4960
-4.250 -0.0738 0.01568 0.00874 -0.0817 0.6123 0.5301
-4.000 -0.0459 0.01611 0.00908 -0.0814 0.6101 0.5542
-3.750 -0.0185 0.01667 0.00959 -0.0810 0.6077 0.5744
-3.500 0.0086 0.01714 0.01007 -0.0805 0.6046 0.5903
-3.250 0.0355 0.01766 0.01059 -0.0799 0.6017 0.6053
-3.000 0.0625 0.01813 0.01104 -0.0793 0.5993 0.6186
-2.750 0.0903 0.01836 0.01115 -0.0794 0.5971 0.6296
-2.500 0.1181 0.01852 0.01127 -0.0792 0.5951 0.6343
-2.250 0.1465 0.01870 0.01133 -0.0794 0.5933 0.6406
-2.000 0.1737 0.01881 0.01141 -0.0797 0.5910 0.6472
-1.750 0.2002 0.01904 0.01167 -0.0794 0.5882 0.6533
-1.500 0.2280 0.01916 0.01171 -0.0797 0.5856 0.6618
-1.250 0.2551 0.01927 0.01182 -0.0797 0.5832 0.6659
-1.000 0.2831 0.01936 0.01185 -0.0799 0.5812 0.6708
-0.750 0.3122 0.01943 0.01179 -0.0806 0.5795 0.6773
-0.500 0.3399 0.01957 0.01190 -0.0807 0.5779 0.6807
-0.250 0.3667 0.01980 0.01213 -0.0809 0.5759 0.6852
0.000 0.3934 0.02000 0.01235 -0.0813 0.5733 0.6911
0.250 0.4200 0.02015 0.01252 -0.0815 0.5707 0.6954
0.500 0.4470 0.02030 0.01267 -0.0816 0.5684 0.6994
0.750 0.4749 0.02046 0.01280 -0.0820 0.5664 0.7046
1.000 0.5032 0.02060 0.01289 -0.0825 0.5647 0.7099
1.250 0.5307 0.02077 0.01305 -0.0826 0.5632 0.7140
1.500 0.5589 0.02102 0.01326 -0.0830 0.5617 0.7187
1.750 0.5843 0.02142 0.01371 -0.0833 0.5593 0.7243
2.000 0.6079 0.02178 0.01419 -0.0831 0.5564 0.7282
2.250 0.6332 0.02210 0.01457 -0.0832 0.5539 0.7331
2.500 0.6603 0.02240 0.01487 -0.0836 0.5519 0.7386
2.750 0.6874 0.02261 0.01510 -0.0838 0.5502 0.7428
3.000 0.7145 0.02282 0.01534 -0.0840 0.5486 0.7474
3.250 0.7430 0.02303 0.01552 -0.0845 0.5471 0.7530
3.500 0.7715 0.02331 0.01577 -0.0849 0.5457 0.7578
3.750 0.7879 0.02422 0.01693 -0.0841 0.5420 0.7623
4.000 0.8094 0.02496 0.01777 -0.0840 0.5392 0.7677
4.250 0.8334 0.02546 0.01834 -0.0841 0.5368 0.7729
4.500 0.8593 0.02571 0.01866 -0.0841 0.5349 0.7780
4.750 0.8881 0.02585 0.01880 -0.0846 0.5333 0.7838
5.000 0.9163 0.02601 0.01898 -0.0849 0.5319 0.7891
5.250 0.9438 0.02630 0.01931 -0.0852 0.5306 0.7949
5.500 0.9471 0.02845 0.02175 -0.0835 0.5254 0.8014
5.750 0.9628 0.02942 0.02288 -0.0827 0.5217 0.8071
6.000 0.9866 0.02989 0.02343 -0.0827 0.5197 0.8142
6.250 1.0138 0.03006 0.02366 -0.0828 0.5181 0.8210
6.500 1.0438 0.03001 0.02366 -0.0832 0.5169 0.8288
6.750 1.0736 0.03001 0.02370 -0.0836 0.5157 0.8369
7.250 0.9786 0.04179 0.03612 -0.0735 0.4948 0.8599
7.500 1.0254 0.04007 0.03447 -0.0742 0.4957 0.8739
7.750 1.0764 0.03823 0.03273 -0.0757 0.4968 0.8937
8.000 1.1319 0.03622 0.03085 -0.0778 0.4980 0.9439
8.250 1.1923 0.03436 0.02896 -0.0813 0.4993 1.0002
8.500 1.0900 0.04438 0.03918 -0.0733 0.4835 1.0002
8.750 1.1372 0.04293 0.03778 -0.0746 0.4838 1.0002
9.000 1.2211 0.03861 0.03348 -0.0786 0.4855 1.0002
9.500 1.3334 0.03178 0.02664 -0.0820 0.4746 1.0002
9.750 1.4113 0.02744 0.02215 -0.0865 0.4712 1.0002
10.000 1.4203 0.02803 0.02291 -0.0844 0.4648 1.0002
10.250 1.4666 0.02556 0.02038 -0.0857 0.4571 1.0002
10.500 1.4807 0.02521 0.02015 -0.0837 0.4477 1.0002
10.750 1.5010 0.02410 0.01907 -0.0820 0.4354 1.0002
11.000 1.5052 0.02392 0.01897 -0.0785 0.4208 1.0002
11.250 1.5023 0.02459 0.01971 -0.0750 0.4019 1.0002
11.500 1.4929 0.02625 0.02137 -0.0720 0.3747 1.0002
11.750 1.4731 0.02941 0.02433 -0.0694 0.3335 1.0002
12.000 1.4439 0.03416 0.02886 -0.0674 0.2965 1.0002
12.250 1.4125 0.03954 0.03408 -0.0658 0.2659 1.0002
12.500 1.3807 0.04508 0.03946 -0.0644 0.2370 1.0002
12.750 1.3492 0.05066 0.04489 -0.0630 0.2074 1.0002
13.000 1.3174 0.05658 0.05063 -0.0620 0.1768 1.0002
13.250 1.2870 0.06261 0.05645 -0.0612 0.1452 1.0002
13.500 1.2586 0.06864 0.06225 -0.0607 0.1123 1.0002
13.750 1.2348 0.07432 0.06772 -0.0603 0.0868 1.0002
14.000 1.2187 0.07924 0.07252 -0.0601 0.0721 1.0002
14.250 1.2078 0.08365 0.07689 -0.0600 0.0639 1.0002
14.500 1.2003 0.08769 0.08092 -0.0600 0.0582 1.0002
14.750 1.1945 0.09154 0.08479 -0.0600 0.0539 1.0002
15.000 1.1936 0.09477 0.08807 -0.0600 0.0499 1.0002
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