FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 200,000 Max Cl/Cd: 70.98 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61168-il-200000.txt Download as CSV file: xf-fx61168-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4095 0.08762 0.08438 -0.0653 1.0000 0.0532
-10.250 -0.4330 0.08285 0.07961 -0.0671 1.0000 0.0532
-10.000 -0.4609 0.07913 0.07589 -0.0673 1.0000 0.0533
-9.750 -0.4877 0.07672 0.07354 -0.0652 1.0000 0.0532
-9.500 -0.5019 0.07183 0.06833 -0.0756 0.9844 0.0537
-9.000 -0.4691 0.05872 0.05528 -0.0837 0.9633 0.0579
-8.750 -0.4554 0.05461 0.05100 -0.0877 0.9430 0.0607
-8.500 -0.4535 0.04972 0.04540 -0.0938 0.9218 0.0683
-8.250 -0.4163 0.04564 0.04142 -0.0977 0.9112 0.0722
-8.000 -0.3854 0.04143 0.03666 -0.1043 0.8963 0.0831
-7.750 -0.3437 0.02953 0.02308 -0.1041 0.8849 0.0317
-7.500 -0.2992 0.02617 0.01929 -0.1079 0.8697 0.0311
-7.250 -0.2580 0.02446 0.01718 -0.1107 0.8528 0.0324
-7.000 -0.2227 0.02267 0.01512 -0.1121 0.8372 0.0337
-6.750 -0.1906 0.02102 0.01340 -0.1124 0.8236 0.0352
-6.500 -0.1628 0.02010 0.01239 -0.1123 0.8112 0.0368
-6.250 -0.1394 0.01936 0.01156 -0.1115 0.7998 0.0393
-6.000 -0.1171 0.01889 0.01098 -0.1107 0.7895 0.0424
-5.750 -0.0999 0.01784 0.00993 -0.1097 0.7813 0.0473
-5.500 -0.0813 0.01722 0.00924 -0.1087 0.7723 0.0528
-5.250 -0.0614 0.01637 0.00833 -0.1084 0.7652 0.0651
-5.000 -0.0494 0.01403 0.00690 -0.1087 0.7574 0.2303
-4.750 -0.0271 0.01291 0.00716 -0.1092 0.7518 0.5537
-4.500 -0.0008 0.01354 0.00775 -0.1081 0.7455 0.5938
-4.250 0.0254 0.01447 0.00860 -0.1066 0.7398 0.6157
-4.000 0.0521 0.01558 0.00958 -0.1051 0.7348 0.6367
-3.750 0.0717 0.01708 0.01115 -0.1008 0.7290 0.6474
-3.500 0.0952 0.01812 0.01213 -0.0980 0.7241 0.6567
-3.250 0.1246 0.01812 0.01194 -0.0989 0.7196 0.6673
-3.000 0.1476 0.01835 0.01214 -0.0973 0.7142 0.6698
-2.750 0.1732 0.01853 0.01224 -0.0965 0.7095 0.6734
-2.500 0.2052 0.01833 0.01183 -0.0984 0.7056 0.6826
-2.250 0.2272 0.01851 0.01202 -0.0968 0.7008 0.6850
-2.000 0.2518 0.01864 0.01209 -0.0959 0.6961 0.6887
-1.750 0.2843 0.01841 0.01169 -0.0980 0.6921 0.6974
-1.500 0.3085 0.01856 0.01181 -0.0969 0.6883 0.6997
-1.250 0.3313 0.01866 0.01191 -0.0958 0.6834 0.7029
-1.000 0.3591 0.01863 0.01181 -0.0961 0.6788 0.7087
-0.750 0.3887 0.01865 0.01171 -0.0967 0.6750 0.7143
-0.500 0.4095 0.01879 0.01189 -0.0951 0.6701 0.7179
-0.250 0.4359 0.01879 0.01186 -0.0951 0.6656 0.7231
0.000 0.4674 0.01868 0.01166 -0.0966 0.6616 0.7285
0.250 0.4926 0.01877 0.01172 -0.0960 0.6579 0.7311
0.500 0.5153 0.01882 0.01181 -0.0951 0.6530 0.7347
0.750 0.5450 0.01878 0.01174 -0.0961 0.6487 0.7397
1.000 0.5761 0.01875 0.01163 -0.0973 0.6451 0.7438
1.250 0.5987 0.01884 0.01176 -0.0962 0.6407 0.7464
1.500 0.6230 0.01887 0.01183 -0.0958 0.6356 0.7499
1.750 0.6539 0.01885 0.01176 -0.0969 0.6312 0.7541
2.000 0.6855 0.01886 0.01172 -0.0982 0.6268 0.7583
2.250 0.7062 0.01890 0.01185 -0.0969 0.6212 0.7608
2.500 0.7331 0.01891 0.01187 -0.0969 0.6166 0.7637
2.750 0.7649 0.01897 0.01185 -0.0980 0.6129 0.7672
3.000 0.7923 0.01903 0.01201 -0.0987 0.6067 0.7719
3.250 0.8177 0.01903 0.01204 -0.0984 0.6019 0.7744
3.500 0.8465 0.01907 0.01205 -0.0987 0.5981 0.7768
3.750 0.8685 0.01917 0.01227 -0.0979 0.5919 0.7799
4.000 0.8974 0.01917 0.01228 -0.0984 0.5863 0.7836
4.250 0.9336 0.01919 0.01224 -0.1006 0.5816 0.7873
4.500 0.9527 0.01922 0.01242 -0.0991 0.5745 0.7896
4.750 0.9795 0.01919 0.01241 -0.0990 0.5695 0.7921
5.000 1.0055 0.01926 0.01255 -0.0989 0.5639 0.7952
5.250 1.0318 0.01927 0.01263 -0.0990 0.5569 0.7987
5.500 1.0677 0.01920 0.01249 -0.1009 0.5517 0.8018
5.750 1.0868 0.01921 0.01269 -0.0995 0.5433 0.8043
6.000 1.1150 0.01906 0.01252 -0.0995 0.5373 0.8070
6.250 1.1354 0.01909 0.01270 -0.0984 0.5287 0.8101
6.500 1.1661 0.01896 0.01255 -0.0991 0.5221 0.8130
6.750 1.1897 0.01901 0.01276 -0.0988 0.5129 0.8163
7.000 1.2173 0.01891 0.01265 -0.0989 0.5057 0.8190
7.250 1.2364 0.01890 0.01280 -0.0974 0.4962 0.8217
7.500 1.2595 0.01889 0.01287 -0.0967 0.4871 0.8244
7.750 1.2845 0.01889 0.01291 -0.0964 0.4782 0.8276
8.000 1.3069 0.01900 0.01315 -0.0958 0.4674 0.8309
8.250 1.3279 0.01905 0.01326 -0.0949 0.4559 0.8337
8.500 1.3466 0.01911 0.01339 -0.0933 0.4439 0.8363
8.750 1.3649 0.01925 0.01357 -0.0919 0.4312 0.8394
9.000 1.3819 0.01947 0.01383 -0.0903 0.4169 0.8430
9.250 1.3971 0.01980 0.01419 -0.0885 0.4004 0.8465
9.500 1.4055 0.02012 0.01456 -0.0854 0.3841 0.8494
9.750 1.4122 0.02057 0.01505 -0.0822 0.3665 0.8527
10.000 1.4187 0.02121 0.01568 -0.0792 0.3481 0.8566
10.250 1.4242 0.02204 0.01649 -0.0764 0.3288 0.8608
10.500 1.4259 0.02294 0.01743 -0.0731 0.3085 0.8647
10.750 1.4247 0.02410 0.01857 -0.0697 0.2881 0.8688
11.000 1.4229 0.02558 0.02001 -0.0669 0.2679 0.8732
11.250 1.4214 0.02726 0.02169 -0.0646 0.2471 0.8776
11.500 1.4155 0.02919 0.02361 -0.0619 0.2290 0.8826
11.750 1.4110 0.03139 0.02579 -0.0600 0.2121 0.8884
12.000 1.4065 0.03371 0.02812 -0.0584 0.1959 0.8943
12.250 1.4009 0.03623 0.03064 -0.0569 0.1809 0.9008
12.500 1.3955 0.03893 0.03334 -0.0557 0.1669 0.9078
12.750 1.3891 0.04162 0.03606 -0.0544 0.1531 0.9168
13.000 1.3808 0.04442 0.03888 -0.0530 0.1397 0.9297
13.250 1.3690 0.04712 0.04164 -0.0513 0.1280 1.0000
13.500 1.3662 0.05073 0.04521 -0.0521 0.1128 1.0000
13.750 1.3636 0.05439 0.04886 -0.0529 0.0986 1.0000
14.000 1.3594 0.05830 0.05273 -0.0538 0.0861 1.0000
14.250 1.3552 0.06231 0.05672 -0.0548 0.0754 1.0000
14.500 1.3530 0.06618 0.06061 -0.0558 0.0660 1.0000
14.750 1.3502 0.07016 0.06461 -0.0569 0.0587 1.0000
15.000 1.3432 0.07477 0.06920 -0.0581 0.0528 1.0000
15.250 1.3438 0.07847 0.07301 -0.0593 0.0466 1.0000
15.500 1.3371 0.08321 0.07776 -0.0607 0.0420 1.0000
15.750 1.3349 0.08742 0.08206 -0.0621 0.0366 1.0000
16.000 1.3262 0.09266 0.08734 -0.0638 0.0319 1.0000
16.250 1.3167 0.09815 0.09288 -0.0658 0.0273 1.0000
16.500 1.3059 0.10391 0.09874 -0.0679 0.0235 1.0000
16.750 1.2977 0.10938 0.10428 -0.0701 0.0209 1.0000
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