FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=1,000,000 Ncrit=0
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61163-il-1000000.txt Download as CSV file: xf-fx61163-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4123 0.13682 0.13513 -0.0297 1.0001 0.0086
-13.250 -0.4106 0.13235 0.13067 -0.0315 1.0001 0.0090
-13.000 -0.4106 0.12715 0.12549 -0.0335 1.0001 0.0094
-12.750 -0.4125 0.11959 0.11795 -0.0367 1.0001 0.0101
-12.500 -0.4144 0.11366 0.11203 -0.0392 1.0001 0.0101
-12.250 -0.4186 0.10709 0.10548 -0.0419 1.0001 0.0102
-11.750 -0.4550 0.08312 0.08143 -0.0547 1.0001 0.0102
-11.500 -0.4770 0.07490 0.07312 -0.0603 1.0001 0.0102
-11.250 -0.4979 0.06858 0.06670 -0.0640 1.0001 0.0102
-11.000 -0.5185 0.06342 0.06145 -0.0662 1.0001 0.0102
-10.750 -0.5386 0.05906 0.05699 -0.0673 1.0001 0.0102
-10.500 -0.5481 0.05363 0.05138 -0.0722 0.9901 0.0102
-10.250 -0.5400 0.04703 0.04444 -0.0829 0.9486 0.0102
-9.000 -0.4915 0.00909 0.00394 -0.0867 0.7105 0.0076
-8.750 -0.4734 0.00752 0.00217 -0.0858 0.6996 0.0076
-8.500 -0.4540 0.00641 0.00092 -0.0850 0.6900 0.0078
-8.250 -0.4334 0.00564 0.00006 -0.0845 0.6815 0.0079
-8.000 -0.4116 0.00515 -0.00051 -0.0843 0.6740 0.0082
-7.750 -0.3896 0.00466 -0.00108 -0.0840 0.6673 0.0085
-7.500 -0.3850 0.01587 0.00981 -0.0867 0.6699 0.0086
-7.250 -0.3608 0.01524 0.00910 -0.0866 0.6633 0.0088
-7.000 -0.3359 0.01462 0.00842 -0.0867 0.6579 0.0090
-6.750 -0.3104 0.01400 0.00774 -0.0869 0.6527 0.0091
-6.500 -0.2845 0.01345 0.00711 -0.0872 0.6479 0.0093
-6.250 -0.2575 0.01295 0.00655 -0.0877 0.6436 0.0096
-6.000 -0.2298 0.01254 0.00609 -0.0882 0.6393 0.0099
-5.750 -0.2018 0.01216 0.00565 -0.0887 0.6350 0.0101
-5.500 -0.1737 0.01163 0.00503 -0.0894 0.6309 0.0104
-5.250 -0.1444 0.01106 0.00439 -0.0903 0.6277 0.0111
-5.000 -0.1149 0.01074 0.00405 -0.0910 0.6240 0.0121
-4.750 -0.0855 0.01050 0.00376 -0.0917 0.6202 0.0134
-4.500 -0.0559 0.01024 0.00344 -0.0924 0.6166 0.0164
-4.250 -0.0246 0.00964 0.00305 -0.0938 0.6136 0.0655
-4.000 0.0109 0.00841 0.00250 -0.0971 0.6105 0.2442
-3.750 0.0508 0.00713 0.00199 -0.1015 0.6073 0.4624
-3.500 0.0839 0.00685 0.00189 -0.1030 0.6043 0.5313
-3.250 0.1150 0.00681 0.00190 -0.1038 0.6010 0.5695
-3.000 0.1456 0.00681 0.00193 -0.1045 0.5982 0.5902
-2.750 0.1758 0.00687 0.00199 -0.1049 0.5950 0.6070
-2.500 0.2057 0.00695 0.00205 -0.1053 0.5916 0.6186
-2.250 0.2355 0.00705 0.00208 -0.1058 0.5884 0.6256
-2.000 0.2652 0.00712 0.00209 -0.1062 0.5853 0.6293
-1.750 0.2951 0.00713 0.00211 -0.1067 0.5831 0.6321
-1.500 0.3249 0.00716 0.00213 -0.1071 0.5804 0.6355
-1.250 0.3548 0.00721 0.00214 -0.1076 0.5775 0.6393
-1.000 0.3847 0.00727 0.00215 -0.1081 0.5746 0.6425
-0.750 0.4139 0.00733 0.00218 -0.1084 0.5715 0.6455
-0.500 0.4434 0.00737 0.00223 -0.1088 0.5684 0.6483
-0.250 0.4731 0.00740 0.00226 -0.1093 0.5650 0.6512
0.000 0.5028 0.00744 0.00228 -0.1097 0.5617 0.6538
0.250 0.5324 0.00750 0.00230 -0.1102 0.5587 0.6560
0.500 0.5618 0.00757 0.00233 -0.1106 0.5554 0.6582
0.750 0.5913 0.00757 0.00237 -0.1110 0.5528 0.6603
1.000 0.6207 0.00760 0.00241 -0.1114 0.5495 0.6623
1.250 0.6500 0.00764 0.00245 -0.1118 0.5461 0.6644
1.500 0.6792 0.00771 0.00251 -0.1122 0.5427 0.6665
1.750 0.7085 0.00778 0.00257 -0.1126 0.5392 0.6687
2.000 0.7381 0.00781 0.00261 -0.1131 0.5350 0.6707
2.250 0.7674 0.00784 0.00264 -0.1135 0.5304 0.6725
2.500 0.7961 0.00791 0.00269 -0.1138 0.5262 0.6745
2.750 0.8253 0.00793 0.00276 -0.1142 0.5223 0.6762
3.000 0.8543 0.00796 0.00282 -0.1145 0.5171 0.6780
3.500 0.9120 0.00808 0.00296 -0.1151 0.5056 0.6818
3.750 0.9405 0.00817 0.00303 -0.1154 0.4981 0.6837
4.000 0.9694 0.00823 0.00310 -0.1158 0.4897 0.6853
4.250 0.9976 0.00834 0.00318 -0.1160 0.4805 0.6866
4.500 1.0258 0.00840 0.00325 -0.1163 0.4700 0.6886
4.750 1.0539 0.00850 0.00337 -0.1165 0.4601 0.6902
5.000 1.0814 0.00864 0.00350 -0.1166 0.4494 0.6919
5.250 1.1087 0.00880 0.00364 -0.1167 0.4380 0.6934
5.500 1.1362 0.00894 0.00380 -0.1168 0.4270 0.6950
5.750 1.1632 0.00913 0.00397 -0.1168 0.4144 0.6968
6.000 1.1886 0.00945 0.00420 -0.1166 0.3933 0.6985
6.250 1.2136 0.00979 0.00445 -0.1164 0.3687 0.7001
6.500 1.2385 0.01015 0.00472 -0.1161 0.3489 0.7014
6.750 1.2635 0.01045 0.00498 -0.1159 0.3289 0.7034
7.000 1.2867 0.01089 0.00532 -0.1154 0.3024 0.7051
7.250 1.3072 0.01153 0.00578 -0.1144 0.2656 0.7068
7.500 1.3258 0.01229 0.00632 -0.1132 0.2250 0.7085
7.750 1.3431 0.01312 0.00694 -0.1118 0.1859 0.7102
8.000 1.3603 0.01391 0.00756 -0.1103 0.1540 0.7119
8.250 1.3769 0.01470 0.00819 -0.1088 0.1265 0.7136
8.500 1.3932 0.01546 0.00882 -0.1073 0.1025 0.7151
9.250 1.4322 0.01787 0.01096 -0.1010 0.0492 0.7198
9.500 1.4417 0.01863 0.01169 -0.0983 0.0378 0.7215
9.750 1.4484 0.01964 0.01265 -0.0954 0.0259 0.7234
10.000 1.4578 0.02055 0.01355 -0.0931 0.0201 0.7251
10.250 1.4658 0.02159 0.01460 -0.0907 0.0151 0.7268
10.500 1.4726 0.02278 0.01580 -0.0885 0.0107 0.7285
10.750 1.4764 0.02430 0.01732 -0.0863 0.0057 0.7300
11.000 1.4823 0.02582 0.01888 -0.0847 0.0042 0.7315
11.250 1.4903 0.02733 0.02047 -0.0835 0.0038 0.7335
11.500 1.4974 0.02901 0.02225 -0.0825 0.0035 0.7355
11.750 1.5037 0.03087 0.02419 -0.0816 0.0033 0.7374
12.000 1.5089 0.03289 0.02630 -0.0808 0.0030 0.7392
12.250 1.5131 0.03506 0.02855 -0.0801 0.0029 0.7410
12.500 1.5162 0.03739 0.03098 -0.0794 0.0028 0.7428
12.750 1.5200 0.03965 0.03332 -0.0788 0.0027 0.7445
13.000 1.5228 0.04203 0.03578 -0.0783 0.0027 0.7460
13.250 1.5244 0.04457 0.03842 -0.0778 0.0026 0.7481
13.500 1.5244 0.04728 0.04124 -0.0772 0.0026 0.7502
13.750 1.5239 0.05005 0.04410 -0.0767 0.0026 0.7523
14.000 1.5231 0.05291 0.04705 -0.0763 0.0025 0.7544
14.250 1.5212 0.05596 0.05020 -0.0760 0.0025 0.7565
14.500 1.5184 0.05916 0.05351 -0.0758 0.0025 0.7584
14.750 1.5161 0.06239 0.05683 -0.0756 0.0024 0.7602
15.000 1.5133 0.06577 0.06031 -0.0756 0.0024 0.7624
15.250 1.5093 0.06937 0.06402 -0.0758 0.0024 0.7647
15.500 1.5045 0.07311 0.06787 -0.0760 0.0023 0.7669
15.750 1.4993 0.07700 0.07186 -0.0763 0.0023 0.7693
16.000 1.4939 0.08099 0.07596 -0.0768 0.0023 0.7718
16.250 1.4876 0.08518 0.08024 -0.0773 0.0023 0.7742
16.500 1.4814 0.08938 0.08455 -0.0780 0.0023 0.7767
16.750 1.4746 0.09377 0.08906 -0.0789 0.0023 0.7795
17.000 1.4674 0.09828 0.09368 -0.0798 0.0022 0.7826
17.250 1.4587 0.10312 0.09863 -0.0810 0.0022 0.7860
17.500 1.4499 0.10797 0.10360 -0.0823 0.0022 0.7894
17.750 1.4414 0.11286 0.10861 -0.0837 0.0022 0.7932
18.000 1.4338 0.11770 0.11356 -0.0853 0.0022 0.7977
18.250 1.4251 0.12281 0.11878 -0.0871 0.0022 0.8026
18.500 1.4157 0.12810 0.12420 -0.0891 0.0022 0.8077
18.750 1.4083 0.13307 0.12928 -0.0912 0.0021 0.8145
19.000 1.4003 0.13825 0.13458 -0.0934 0.0021 0.8223
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