WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.86 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617ai-il-1000000.txt Download as CSV file: xf-fx6617ai-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7108 0.09465 0.09253 -0.0465 0.9998 0.0105
-16.000 -0.7360 0.08538 0.08311 -0.0523 0.9998 0.0105
-15.750 -0.7593 0.07705 0.07462 -0.0575 0.9998 0.0104
-15.500 -0.7801 0.06975 0.06716 -0.0620 0.9998 0.0104
-15.250 -0.8010 0.06296 0.06020 -0.0660 0.9998 0.0105
-15.000 -0.8178 0.05712 0.05378 -0.0698 0.8384 0.0106
-14.750 -0.8313 0.05277 0.04905 -0.0716 0.7767 0.0106
-14.500 -0.8396 0.04899 0.04500 -0.0732 0.7396 0.0107
-14.250 -0.8430 0.04587 0.04168 -0.0745 0.7115 0.0108
-14.000 -0.8430 0.04316 0.03880 -0.0756 0.6892 0.0109
-13.500 -0.8358 0.03864 0.03401 -0.0773 0.6589 0.0112
-13.250 -0.8300 0.03664 0.03188 -0.0781 0.6483 0.0113
-13.000 -0.8229 0.03479 0.02991 -0.0787 0.6391 0.0114
-12.750 -0.8148 0.03302 0.02803 -0.0793 0.6312 0.0116
-12.500 -0.8054 0.03139 0.02627 -0.0798 0.6240 0.0118
-12.250 -0.7947 0.02985 0.02463 -0.0801 0.6180 0.0120
-12.000 -0.7827 0.02844 0.02309 -0.0805 0.6122 0.0123
-11.750 -0.7694 0.02710 0.02163 -0.0808 0.6072 0.0125
-11.500 -0.7547 0.02586 0.02030 -0.0812 0.6029 0.0128
-11.250 -0.7407 0.02488 0.01919 -0.0812 0.5986 0.0130
-11.000 -0.7234 0.02415 0.01835 -0.0809 0.5943 0.0132
-10.750 -0.7030 0.02358 0.01768 -0.0810 0.5908 0.0134
-10.500 -0.6908 0.02149 0.01544 -0.0801 0.5878 0.0139
-10.250 -0.6714 0.02056 0.01446 -0.0799 0.5845 0.0143
-10.000 -0.6492 0.02000 0.01385 -0.0799 0.5810 0.0147
-9.750 -0.6262 0.01951 0.01330 -0.0799 0.5771 0.0150
-9.500 -0.6025 0.01897 0.01272 -0.0800 0.5747 0.0154
-9.250 -0.5788 0.01841 0.01210 -0.0800 0.5719 0.0158
-9.000 -0.5551 0.01782 0.01146 -0.0799 0.5690 0.0161
-8.750 -0.5311 0.01726 0.01083 -0.0798 0.5663 0.0164
-8.500 -0.5070 0.01674 0.01023 -0.0798 0.5634 0.0166
-8.250 -0.4823 0.01625 0.00967 -0.0798 0.5607 0.0169
-8.000 -0.4570 0.01577 0.00915 -0.0798 0.5588 0.0170
-7.750 -0.4314 0.01533 0.00866 -0.0799 0.5566 0.0172
-7.500 -0.4081 0.01454 0.00781 -0.0798 0.5544 0.0176
-7.250 -0.3841 0.01385 0.00706 -0.0797 0.5520 0.0183
-7.000 -0.3580 0.01348 0.00665 -0.0798 0.5495 0.0190
-6.750 -0.3317 0.01315 0.00625 -0.0799 0.5466 0.0195
-6.500 -0.3048 0.01281 0.00587 -0.0801 0.5446 0.0201
-6.250 -0.2776 0.01248 0.00551 -0.0803 0.5430 0.0207
-6.000 -0.2500 0.01220 0.00520 -0.0805 0.5411 0.0215
-5.750 -0.2225 0.01191 0.00486 -0.0807 0.5391 0.0222
-5.500 -0.1954 0.01154 0.00446 -0.0808 0.5372 0.0243
-5.250 -0.1676 0.01133 0.00422 -0.0811 0.5352 0.0264
-5.000 -0.1399 0.01110 0.00396 -0.0813 0.5331 0.0298
-4.750 -0.1123 0.01092 0.00375 -0.0815 0.5304 0.0357
-4.500 -0.0847 0.01057 0.00348 -0.0817 0.5289 0.0521
-4.250 -0.0584 0.01000 0.00317 -0.0820 0.5274 0.1130
-4.000 -0.0324 0.00939 0.00287 -0.0822 0.5257 0.1946
-3.750 -0.0063 0.00879 0.00260 -0.0825 0.5240 0.2839
-3.500 0.0196 0.00819 0.00237 -0.0827 0.5223 0.3906
-3.250 0.0477 0.00798 0.00229 -0.0830 0.5206 0.4412
-3.000 0.0762 0.00788 0.00224 -0.0833 0.5189 0.4720
-2.750 0.1048 0.00784 0.00224 -0.0836 0.5169 0.4966
-2.500 0.1337 0.00787 0.00227 -0.0839 0.5146 0.5179
-2.250 0.1631 0.00785 0.00226 -0.0843 0.5134 0.5303
-2.000 0.1925 0.00785 0.00228 -0.0847 0.5119 0.5438
-1.750 0.2219 0.00787 0.00231 -0.0850 0.5104 0.5568
-1.500 0.2515 0.00792 0.00232 -0.0855 0.5088 0.5643
-1.250 0.2809 0.00792 0.00232 -0.0859 0.5072 0.5695
-1.000 0.3103 0.00796 0.00234 -0.0863 0.5057 0.5752
-0.750 0.3398 0.00802 0.00235 -0.0867 0.5041 0.5805
-0.500 0.3689 0.00806 0.00238 -0.0871 0.5024 0.5858
-0.250 0.3980 0.00816 0.00245 -0.0874 0.5003 0.5908
0.000 0.4274 0.00822 0.00249 -0.0879 0.4988 0.5951
0.250 0.4570 0.00823 0.00250 -0.0883 0.4976 0.5985
0.500 0.4863 0.00824 0.00252 -0.0888 0.4963 0.6022
0.750 0.5156 0.00827 0.00256 -0.0892 0.4949 0.6059
1.000 0.5450 0.00832 0.00260 -0.0896 0.4934 0.6094
1.250 0.5744 0.00837 0.00263 -0.0901 0.4920 0.6125
1.500 0.6036 0.00839 0.00266 -0.0905 0.4905 0.6158
1.750 0.6326 0.00843 0.00270 -0.0909 0.4890 0.6191
2.000 0.6616 0.00851 0.00277 -0.0913 0.4872 0.6224
2.250 0.6905 0.00864 0.00287 -0.0917 0.4851 0.6258
2.500 0.7197 0.00871 0.00295 -0.0922 0.4839 0.6287
2.750 0.7488 0.00872 0.00300 -0.0926 0.4828 0.6319
3.000 0.7779 0.00875 0.00307 -0.0930 0.4816 0.6349
3.250 0.8069 0.00880 0.00314 -0.0934 0.4802 0.6381
3.500 0.8359 0.00886 0.00322 -0.0939 0.4787 0.6413
3.750 0.8649 0.00892 0.00328 -0.0943 0.4771 0.6443
4.000 0.8937 0.00896 0.00335 -0.0947 0.4756 0.6474
4.250 0.9224 0.00902 0.00344 -0.0951 0.4742 0.6505
4.500 0.9510 0.00911 0.00355 -0.0955 0.4727 0.6536
4.750 0.9795 0.00925 0.00369 -0.0958 0.4707 0.6568
5.000 1.0082 0.00937 0.00382 -0.0962 0.4691 0.6600
5.250 1.0368 0.00940 0.00392 -0.0966 0.4680 0.6632
5.500 1.0653 0.00945 0.00403 -0.0970 0.4667 0.6664
5.750 1.0937 0.00951 0.00414 -0.0974 0.4649 0.6698
6.000 1.1221 0.00954 0.00421 -0.0977 0.4625 0.6734
6.250 1.1504 0.00960 0.00429 -0.0980 0.4601 0.6767
6.500 1.1778 0.00968 0.00439 -0.0983 0.4561 0.6804
6.750 1.2057 0.00970 0.00448 -0.0985 0.4525 0.6842
7.000 1.2338 0.00970 0.00454 -0.0988 0.4486 0.6883
7.250 1.2613 0.00975 0.00460 -0.0990 0.4435 0.6923
7.500 1.2882 0.00986 0.00475 -0.0992 0.4395 0.6967
7.750 1.3162 0.00989 0.00487 -0.0995 0.4359 0.7015
8.000 1.3437 0.00996 0.00499 -0.0997 0.4314 0.7064
8.250 1.3697 0.01011 0.00515 -0.0997 0.4255 0.7113
8.500 1.3972 0.01015 0.00529 -0.1000 0.4182 0.7167
8.750 1.4227 0.01032 0.00545 -0.0999 0.4064 0.7225
9.000 1.4459 0.01061 0.00570 -0.0995 0.3860 0.7281
9.250 1.4621 0.01134 0.00626 -0.0981 0.3456 0.7348
9.500 1.4592 0.01318 0.00766 -0.0939 0.2716 0.7419
9.750 1.4389 0.01547 0.00956 -0.0872 0.1998 0.7502
10.000 1.4157 0.01811 0.01195 -0.0813 0.1473 0.7597
10.250 1.3987 0.02108 0.01481 -0.0778 0.1124 0.7711
10.500 1.3815 0.02490 0.01857 -0.0760 0.0821 0.7851
10.750 1.3692 0.02872 0.02241 -0.0750 0.0616 0.8045
11.000 1.3618 0.03193 0.02579 -0.0740 0.0501 0.8591
11.250 1.3561 0.03472 0.02879 -0.0728 0.0431 1.0002
11.500 1.3518 0.03779 0.03188 -0.0721 0.0376 1.0002
11.750 1.3509 0.04049 0.03462 -0.0714 0.0337 1.0002
12.000 1.3468 0.04346 0.03760 -0.0706 0.0298 1.0002
12.250 1.3466 0.04605 0.04023 -0.0699 0.0275 1.0002
12.500 1.3453 0.04880 0.04300 -0.0692 0.0251 1.0002
12.750 1.3444 0.05158 0.04582 -0.0687 0.0231 1.0002
13.000 1.3470 0.05405 0.04834 -0.0683 0.0219 1.0002
13.250 1.3482 0.05672 0.05103 -0.0679 0.0206 1.0002
13.500 1.3485 0.05948 0.05382 -0.0675 0.0192 1.0002
13.750 1.3503 0.06212 0.05650 -0.0672 0.0181 1.0002
14.000 1.3542 0.06454 0.05897 -0.0669 0.0172 1.0002
14.250 1.3560 0.06725 0.06172 -0.0667 0.0163 1.0002
14.500 1.3572 0.06999 0.06449 -0.0664 0.0152 1.0002
14.750 1.3570 0.07295 0.06750 -0.0662 0.0143 1.0002
15.000 1.3622 0.07530 0.06990 -0.0661 0.0136 1.0002
15.250 1.3656 0.07787 0.07251 -0.0660 0.0129 1.0002
15.500 1.3674 0.08065 0.07533 -0.0659 0.0122 1.0002
15.750 1.3668 0.08368 0.07839 -0.0658 0.0113 1.0002
16.000 1.3701 0.08633 0.08110 -0.0658 0.0109 1.0002
16.250 1.3743 0.08886 0.08367 -0.0659 0.0104 1.0002
16.500 1.3787 0.09137 0.08622 -0.0659 0.0098 1.0002
16.750 1.3804 0.09424 0.08913 -0.0661 0.0092 1.0002
17.000 1.3800 0.09737 0.09229 -0.0662 0.0087 1.0002
17.250 1.3834 0.10001 0.09499 -0.0664 0.0083 1.0002
17.500 1.3858 0.10284 0.09787 -0.0666 0.0079 1.0002
17.750 1.3890 0.10555 0.10063 -0.0669 0.0075 1.0002
18.000 1.3913 0.10838 0.10349 -0.0672 0.0071 1.0002
18.250 1.3888 0.11191 0.10706 -0.0677 0.0066 1.0002
18.500 1.3887 0.11508 0.11029 -0.0682 0.0063 1.0002
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