FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.82 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617a2-il-1000000.txt Download as CSV file: xf-fx6617a2-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7174 0.08076 0.07844 -0.0652 1.0000 0.0076
-16.000 -0.7465 0.07184 0.06932 -0.0703 1.0000 0.0074
-15.750 -0.7539 0.06698 0.06437 -0.0731 1.0000 0.0073
-15.500 -0.7832 0.05924 0.05643 -0.0772 1.0000 0.0074
-15.250 -0.7960 0.05444 0.05150 -0.0795 1.0000 0.0074
-15.000 -0.8116 0.04976 0.04670 -0.0813 1.0000 0.0076
-14.750 -0.8204 0.04623 0.04305 -0.0824 1.0000 0.0077
-14.500 -0.8124 0.04256 0.03926 -0.0862 0.9921 0.0078
-14.250 -0.7303 0.03668 0.03305 -0.1081 0.9220 0.0080
-14.000 -0.6861 0.03392 0.02963 -0.1179 0.8050 0.0082
-13.750 -0.6838 0.03258 0.02806 -0.1169 0.7633 0.0083
-13.500 -0.6771 0.03147 0.02678 -0.1162 0.7343 0.0085
-13.250 -0.6742 0.02995 0.02509 -0.1154 0.7127 0.0086
-13.000 -0.6731 0.02830 0.02327 -0.1143 0.6955 0.0086
-12.750 -0.6656 0.02714 0.02198 -0.1135 0.6811 0.0089
-12.500 -0.6587 0.02593 0.02064 -0.1125 0.6691 0.0089
-12.250 -0.6506 0.02484 0.01943 -0.1115 0.6585 0.0091
-12.000 -0.6431 0.02369 0.01817 -0.1104 0.6492 0.0092
-11.750 -0.6325 0.02281 0.01718 -0.1095 0.6413 0.0094
-11.500 -0.6251 0.02172 0.01599 -0.1081 0.6343 0.0095
-11.250 -0.6175 0.02075 0.01491 -0.1066 0.6276 0.0096
-11.000 -0.6193 0.01939 0.01346 -0.1039 0.6225 0.0098
-10.750 -0.6143 0.01865 0.01265 -0.1011 0.6173 0.0100
-10.500 -0.6036 0.01821 0.01213 -0.0990 0.6119 0.0102
-10.250 -0.5851 0.01784 0.01173 -0.0979 0.6078 0.0105
-10.000 -0.5675 0.01739 0.01124 -0.0968 0.6036 0.0108
-9.750 -0.5476 0.01707 0.01086 -0.0959 0.5995 0.0113
-9.500 -0.5283 0.01668 0.01039 -0.0949 0.5957 0.0117
-9.250 -0.5073 0.01629 0.00995 -0.0941 0.5928 0.0122
-9.000 -0.4889 0.01572 0.00933 -0.0930 0.5896 0.0129
-8.750 -0.4674 0.01537 0.00895 -0.0923 0.5864 0.0135
-8.500 -0.4440 0.01515 0.00870 -0.0918 0.5832 0.0143
-8.250 -0.4196 0.01500 0.00849 -0.0914 0.5800 0.0153
-8.000 -0.3925 0.01496 0.00841 -0.0914 0.5777 0.0160
-7.750 -0.3765 0.01407 0.00749 -0.0900 0.5753 0.0175
-7.500 -0.3523 0.01381 0.00721 -0.0896 0.5725 0.0187
-7.250 -0.3282 0.01354 0.00689 -0.0892 0.5699 0.0196
-7.000 -0.3033 0.01335 0.00665 -0.0889 0.5672 0.0201
-6.750 -0.2833 0.01276 0.00597 -0.0879 0.5646 0.0214
-6.500 -0.2593 0.01240 0.00560 -0.0875 0.5629 0.0224
-6.250 -0.2343 0.01212 0.00530 -0.0872 0.5610 0.0232
-6.000 -0.2090 0.01186 0.00501 -0.0869 0.5590 0.0239
-5.750 -0.1833 0.01164 0.00475 -0.0866 0.5569 0.0247
-5.500 -0.1573 0.01146 0.00453 -0.0865 0.5547 0.0252
-5.250 -0.1328 0.01116 0.00416 -0.0860 0.5524 0.0266
-5.000 -0.1073 0.01098 0.00395 -0.0858 0.5496 0.0283
-4.750 -0.0809 0.01080 0.00375 -0.0856 0.5480 0.0296
-4.500 -0.0541 0.01063 0.00356 -0.0855 0.5465 0.0308
-4.250 -0.0274 0.01045 0.00337 -0.0854 0.5447 0.0329
-4.000 -0.0009 0.01027 0.00319 -0.0853 0.5428 0.0388
-3.750 0.0231 0.00984 0.00295 -0.0848 0.5409 0.0842
-3.500 0.0461 0.00935 0.00272 -0.0843 0.5389 0.1571
-3.250 0.0685 0.00883 0.00249 -0.0837 0.5371 0.2500
-3.000 0.0922 0.00846 0.00232 -0.0832 0.5348 0.3174
-2.750 0.1139 0.00789 0.00214 -0.0825 0.5330 0.4335
-2.500 0.1400 0.00769 0.00211 -0.0822 0.5316 0.4896
-2.250 0.1677 0.00766 0.00211 -0.0823 0.5300 0.5185
-2.000 0.1958 0.00766 0.00214 -0.0824 0.5282 0.5370
-1.750 0.2242 0.00771 0.00218 -0.0825 0.5265 0.5519
-1.500 0.2526 0.00775 0.00222 -0.0826 0.5249 0.5609
-1.250 0.2810 0.00781 0.00223 -0.0828 0.5232 0.5678
-1.000 0.3091 0.00787 0.00229 -0.0829 0.5214 0.5745
-0.750 0.3374 0.00798 0.00234 -0.0831 0.5191 0.5790
-0.500 0.3659 0.00804 0.00237 -0.0833 0.5174 0.5823
-0.250 0.3942 0.00803 0.00238 -0.0834 0.5161 0.5860
0.000 0.4225 0.00808 0.00244 -0.0836 0.5145 0.5912
0.250 0.4510 0.00812 0.00246 -0.0838 0.5130 0.5941
0.500 0.4795 0.00817 0.00248 -0.0840 0.5113 0.5965
0.750 0.5077 0.00818 0.00249 -0.0842 0.5098 0.5993
1.000 0.5358 0.00820 0.00252 -0.0844 0.5081 0.6017
1.250 0.5638 0.00825 0.00256 -0.0845 0.5064 0.6039
1.500 0.5918 0.00834 0.00262 -0.0847 0.5042 0.6061
1.750 0.6200 0.00843 0.00269 -0.0849 0.5023 0.6084
2.000 0.6481 0.00845 0.00273 -0.0851 0.5010 0.6109
2.250 0.6762 0.00849 0.00278 -0.0853 0.4994 0.6130
2.500 0.7041 0.00849 0.00280 -0.0855 0.4975 0.6154
2.750 0.7319 0.00851 0.00284 -0.0856 0.4956 0.6174
3.000 0.7596 0.00854 0.00289 -0.0857 0.4938 0.6195
3.250 0.7873 0.00860 0.00295 -0.0859 0.4921 0.6216
3.500 0.8149 0.00868 0.00303 -0.0860 0.4903 0.6238
3.750 0.8426 0.00882 0.00315 -0.0862 0.4880 0.6257
4.000 0.8703 0.00887 0.00323 -0.0863 0.4867 0.6277
4.250 0.8978 0.00891 0.00330 -0.0865 0.4853 0.6295
4.500 0.9251 0.00892 0.00337 -0.0865 0.4836 0.6321
4.750 0.9522 0.00895 0.00345 -0.0866 0.4816 0.6344
5.000 0.9788 0.00896 0.00348 -0.0865 0.4782 0.6365
5.250 1.0048 0.00903 0.00354 -0.0863 0.4741 0.6388
5.500 1.0315 0.00910 0.00363 -0.0863 0.4714 0.6411
5.750 1.0584 0.00914 0.00373 -0.0864 0.4694 0.6433
6.000 1.0850 0.00919 0.00382 -0.0863 0.4669 0.6455
6.250 1.1107 0.00920 0.00388 -0.0861 0.4630 0.6486
6.500 1.1357 0.00930 0.00398 -0.0858 0.4591 0.6514
6.750 1.1616 0.00936 0.00411 -0.0857 0.4562 0.6547
7.000 1.1877 0.00941 0.00421 -0.0855 0.4529 0.6574
7.250 1.2129 0.00948 0.00431 -0.0853 0.4485 0.6605
7.500 1.2359 0.00957 0.00443 -0.0846 0.4422 0.6642
7.750 1.2607 0.00961 0.00453 -0.0842 0.4351 0.6678
8.000 1.2826 0.00973 0.00465 -0.0834 0.4234 0.6713
8.250 1.3014 0.00996 0.00483 -0.0819 0.4040 0.6747
8.500 1.3164 0.01032 0.00511 -0.0798 0.3825 0.6784
8.750 1.3296 0.01066 0.00541 -0.0774 0.3632 0.6825
9.000 1.3317 0.01127 0.00590 -0.0729 0.3331 0.6868
9.250 1.3278 0.01216 0.00661 -0.0675 0.2988 0.6911
9.500 1.3104 0.01350 0.00773 -0.0602 0.2537 0.6959
9.750 1.2985 0.01477 0.00889 -0.0544 0.2230 0.7017
10.000 1.2803 0.01652 0.01050 -0.0485 0.1908 0.7077
10.250 1.2633 0.01860 0.01250 -0.0437 0.1634 0.7155
10.500 1.2434 0.02136 0.01517 -0.0396 0.1348 0.7247
10.750 1.2313 0.02402 0.01780 -0.0370 0.1146 0.7373
11.000 1.2193 0.02691 0.02070 -0.0349 0.0940 0.7559
11.250 1.2048 0.03024 0.02409 -0.0332 0.0719 0.8000
11.500 1.2628 0.03701 0.03102 -0.0521 0.0275 0.9343
11.750 1.2703 0.03971 0.03371 -0.0529 0.0208 1.0000
12.000 1.2687 0.04236 0.03637 -0.0522 0.0167 1.0000
12.250 1.2703 0.04478 0.03881 -0.0516 0.0153 1.0000
12.500 1.2733 0.04714 0.04120 -0.0512 0.0142 1.0000
12.750 1.2763 0.04950 0.04362 -0.0508 0.0135 1.0000
13.000 1.2807 0.05175 0.04592 -0.0504 0.0132 1.0000
13.250 1.2835 0.05419 0.04842 -0.0501 0.0128 1.0000
13.500 1.2858 0.05670 0.05098 -0.0498 0.0123 1.0000
13.750 1.2876 0.05930 0.05362 -0.0495 0.0119 1.0000
14.000 1.2864 0.06223 0.05661 -0.0491 0.0113 1.0000
14.250 1.2866 0.06508 0.05953 -0.0489 0.0108 1.0000
14.500 1.2925 0.06731 0.06181 -0.0488 0.0106 1.0000
14.750 1.2967 0.06971 0.06427 -0.0487 0.0101 1.0000
15.000 1.2990 0.07238 0.06699 -0.0486 0.0098 1.0000
15.250 1.2998 0.07523 0.06990 -0.0485 0.0096 1.0000
15.500 1.3009 0.07811 0.07283 -0.0485 0.0092 1.0000
15.750 1.3022 0.08094 0.07571 -0.0486 0.0090 1.0000
16.000 1.2928 0.08509 0.07994 -0.0486 0.0084 1.0000
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Polar data table (+)
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