FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.25 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61140-il-1000000-n5.txt Download as CSV file: xf-fx61140-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5406 0.07636 0.07482 -0.0463 1.0000 0.0022
-11.000 -0.7244 0.04042 0.03808 -0.0638 0.9992 0.0021
-10.750 -0.7439 0.03329 0.03048 -0.0678 0.9951 0.0020
-10.500 -0.7457 0.02869 0.02548 -0.0698 0.9896 0.0020
-10.250 -0.7273 0.02519 0.02162 -0.0731 0.9860 0.0020
-10.000 -0.7104 0.02271 0.01885 -0.0740 0.9818 0.0021
-9.750 -0.6900 0.02085 0.01677 -0.0747 0.9767 0.0021
-9.250 -0.6444 0.01817 0.01376 -0.0756 0.9652 0.0021
-9.000 -0.6169 0.01706 0.01251 -0.0766 0.9598 0.0022
-8.750 -0.5914 0.01605 0.01137 -0.0771 0.9507 0.0022
-8.500 -0.5567 0.01512 0.01034 -0.0794 0.9434 0.0023
-8.250 -0.5133 0.01423 0.00933 -0.0834 0.9345 0.0023
-8.000 -0.4598 0.01292 0.00785 -0.0901 0.9224 0.0027
-7.750 -0.3943 0.01226 0.00708 -0.0989 0.9023 0.0031
-7.500 -0.3515 0.01187 0.00647 -0.1026 0.8597 0.0034
-7.250 -0.3262 0.01164 0.00605 -0.1025 0.8222 0.0037
-7.000 -0.3027 0.01144 0.00568 -0.1020 0.7903 0.0040
-6.750 -0.2785 0.01123 0.00531 -0.1016 0.7627 0.0042
-6.500 -0.2536 0.01091 0.00486 -0.1015 0.7385 0.0047
-6.250 -0.2279 0.01071 0.00456 -0.1014 0.7170 0.0054
-6.000 -0.2014 0.01051 0.00427 -0.1014 0.6972 0.0059
-5.750 -0.1744 0.01035 0.00400 -0.1015 0.6788 0.0065
-5.500 -0.1471 0.01016 0.00373 -0.1017 0.6614 0.0076
-5.250 -0.1194 0.01000 0.00350 -0.1020 0.6459 0.0092
-4.750 -0.0628 0.00967 0.00307 -0.1027 0.6182 0.0141
-4.500 -0.0340 0.00953 0.00286 -0.1031 0.6062 0.0172
-4.250 -0.0051 0.00939 0.00267 -0.1036 0.5943 0.0220
-4.000 0.0242 0.00921 0.00250 -0.1041 0.5836 0.0354
-3.750 0.0541 0.00898 0.00232 -0.1049 0.5737 0.0639
-3.500 0.0863 0.00848 0.00207 -0.1066 0.5639 0.1468
-3.250 0.1209 0.00781 0.00179 -0.1090 0.5542 0.2745
-3.000 0.1564 0.00722 0.00156 -0.1115 0.5445 0.4016
-2.750 0.1903 0.00687 0.00144 -0.1133 0.5357 0.4885
-2.500 0.2224 0.00670 0.00141 -0.1146 0.5271 0.5544
-2.250 0.2525 0.00669 0.00141 -0.1151 0.5186 0.5796
-2.000 0.2821 0.00672 0.00141 -0.1155 0.5111 0.5936
-1.750 0.3113 0.00677 0.00142 -0.1159 0.5035 0.6023
-1.500 0.3406 0.00682 0.00142 -0.1162 0.4971 0.6097
-1.250 0.3698 0.00687 0.00144 -0.1165 0.4908 0.6159
-1.000 0.3990 0.00693 0.00146 -0.1168 0.4854 0.6215
-0.750 0.4282 0.00698 0.00147 -0.1171 0.4795 0.6261
-0.500 0.4571 0.00705 0.00151 -0.1174 0.4733 0.6304
-0.250 0.4862 0.00711 0.00154 -0.1177 0.4677 0.6348
0.000 0.5152 0.00717 0.00157 -0.1180 0.4619 0.6387
0.250 0.5440 0.00724 0.00161 -0.1182 0.4566 0.6417
0.500 0.5729 0.00731 0.00166 -0.1185 0.4503 0.6450
1.000 0.6305 0.00747 0.00177 -0.1190 0.4385 0.6522
1.250 0.6592 0.00755 0.00183 -0.1192 0.4326 0.6550
1.500 0.6878 0.00763 0.00190 -0.1195 0.4274 0.6574
1.750 0.7166 0.00770 0.00198 -0.1197 0.4222 0.6599
2.000 0.7451 0.00779 0.00206 -0.1199 0.4171 0.6623
2.250 0.7737 0.00788 0.00214 -0.1201 0.4126 0.6647
2.500 0.8023 0.00796 0.00222 -0.1204 0.4070 0.6671
3.000 0.8591 0.00815 0.00242 -0.1207 0.3962 0.6711
3.250 0.8872 0.00826 0.00253 -0.1209 0.3897 0.6731
3.500 0.9154 0.00837 0.00265 -0.1210 0.3830 0.6753
3.750 0.9434 0.00849 0.00277 -0.1212 0.3758 0.6776
4.000 0.9715 0.00862 0.00290 -0.1213 0.3696 0.6799
4.250 0.9993 0.00876 0.00303 -0.1214 0.3612 0.6819
4.500 1.0269 0.00891 0.00318 -0.1215 0.3510 0.6838
4.750 1.0534 0.00916 0.00337 -0.1214 0.3316 0.6856
5.000 1.0787 0.00955 0.00361 -0.1212 0.3003 0.6874
5.250 1.1022 0.01012 0.00396 -0.1206 0.2547 0.6892
5.500 1.1259 0.01067 0.00433 -0.1201 0.2183 0.6911
5.750 1.1464 0.01157 0.00491 -0.1192 0.1585 0.6930
6.000 1.1636 0.01280 0.00571 -0.1178 0.0864 0.6948
6.250 1.1840 0.01367 0.00635 -0.1168 0.0450 0.6963
6.500 1.2051 0.01443 0.00697 -0.1158 0.0185 0.6979
6.750 1.2288 0.01490 0.00742 -0.1153 0.0107 0.6996
7.000 1.2509 0.01550 0.00801 -0.1145 0.0029 0.7012
7.250 1.2746 0.01593 0.00848 -0.1140 0.0022 0.7030
7.500 1.2984 0.01634 0.00893 -0.1135 0.0020 0.7048
7.750 1.3218 0.01676 0.00940 -0.1129 0.0018 0.7066
8.000 1.3445 0.01722 0.00991 -0.1123 0.0017 0.7085
8.250 1.3666 0.01772 0.01046 -0.1115 0.0015 0.7102
8.500 1.3879 0.01827 0.01107 -0.1106 0.0014 0.7117
8.750 1.4082 0.01885 0.01174 -0.1096 0.0013 0.7132
9.000 1.4272 0.01952 0.01248 -0.1084 0.0012 0.7148
9.250 1.4450 0.02021 0.01325 -0.1070 0.0012 0.7165
9.500 1.4609 0.02100 0.01412 -0.1053 0.0011 0.7182
9.750 1.4720 0.02196 0.01518 -0.1028 0.0011 0.7199
10.000 1.4799 0.02288 0.01619 -0.0998 0.0010 0.7215
10.250 1.4845 0.02402 0.01742 -0.0964 0.0010 0.7231
10.500 1.4890 0.02522 0.01872 -0.0933 0.0010 0.7247
11.000 1.4964 0.02794 0.02166 -0.0878 0.0010 0.7281
11.250 1.4991 0.02953 0.02335 -0.0854 0.0010 0.7297
11.500 1.5007 0.03135 0.02528 -0.0833 0.0010 0.7313
11.750 1.5011 0.03344 0.02749 -0.0816 0.0010 0.7330
12.000 1.5014 0.03575 0.02990 -0.0803 0.0010 0.7346
12.250 1.5004 0.03840 0.03265 -0.0793 0.0010 0.7363
12.500 1.4983 0.04138 0.03575 -0.0787 0.0010 0.7379
12.750 1.4961 0.04459 0.03907 -0.0785 0.0010 0.7394
13.000 1.4937 0.04799 0.04259 -0.0786 0.0010 0.7410
13.250 1.4902 0.05169 0.04642 -0.0789 0.0010 0.7424
13.500 1.4859 0.05564 0.05049 -0.0794 0.0010 0.7437
13.750 1.4823 0.05959 0.05455 -0.0802 0.0009 0.7451
14.000 1.4770 0.06391 0.05900 -0.0811 0.0009 0.7464
14.250 1.4746 0.06795 0.06314 -0.0821 0.0009 0.7478
14.500 1.4687 0.07257 0.06789 -0.0834 0.0009 0.7491
14.750 1.4613 0.07762 0.07305 -0.0849 0.0009 0.7503
15.000 1.4557 0.08253 0.07808 -0.0865 0.0009 0.7516
15.250 1.4488 0.08774 0.08341 -0.0883 0.0009 0.7528
15.750 1.4409 0.09760 0.09350 -0.0922 0.0009 0.7553
16.000 1.4313 0.10370 0.09973 -0.0946 0.0009 0.7564
16.250 1.4257 0.10915 0.10530 -0.0970 0.0009 0.7576
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