FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.24 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61147-il-1000000-n5.txt Download as CSV file: xf-fx61147-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7229 0.05677 0.05463 -0.0684 1.0000 0.0024
-13.000 -0.7555 0.04933 0.04701 -0.0720 1.0000 0.0024
-12.750 -0.7791 0.04439 0.04191 -0.0731 1.0000 0.0024
-12.500 -0.7872 0.03842 0.03565 -0.0788 0.9982 0.0024
-12.250 -0.7798 0.03470 0.03170 -0.0828 0.9956 0.0024
-12.000 -0.7778 0.03109 0.02784 -0.0853 0.9920 0.0024
-11.750 -0.7656 0.02857 0.02512 -0.0876 0.9882 0.0024
-11.500 -0.7519 0.02682 0.02324 -0.0887 0.9837 0.0024
-11.250 -0.7397 0.02456 0.02077 -0.0899 0.9775 0.0024
-11.000 -0.7189 0.02280 0.01885 -0.0916 0.9729 0.0024
-10.750 -0.7010 0.02130 0.01719 -0.0919 0.9659 0.0025
-10.250 -0.6574 0.01892 0.01454 -0.0928 0.9539 0.0025
-10.000 -0.6285 0.01787 0.01336 -0.0942 0.9498 0.0025
-9.750 -0.5996 0.01690 0.01228 -0.0956 0.9436 0.0025
-9.500 -0.5641 0.01596 0.01123 -0.0982 0.9383 0.0026
-9.250 -0.5238 0.01508 0.01024 -0.1017 0.9324 0.0026
-9.000 -0.4808 0.01403 0.00906 -0.1060 0.9232 0.0027
-8.750 -0.4333 0.01323 0.00813 -0.1110 0.9131 0.0028
-8.500 -0.3855 0.01258 0.00737 -0.1160 0.9016 0.0031
-8.250 -0.3478 0.01212 0.00680 -0.1188 0.8868 0.0033
-8.000 -0.3160 0.01175 0.00633 -0.1201 0.8677 0.0036
-7.750 -0.2881 0.01146 0.00591 -0.1205 0.8458 0.0039
-7.500 -0.2632 0.01119 0.00552 -0.1203 0.8218 0.0044
-7.250 -0.2393 0.01098 0.00519 -0.1198 0.7981 0.0050
-7.000 -0.2151 0.01080 0.00491 -0.1193 0.7767 0.0061
-6.750 -0.1907 0.01063 0.00466 -0.1189 0.7569 0.0073
-6.500 -0.1658 0.01049 0.00442 -0.1185 0.7363 0.0082
-6.250 -0.1409 0.01038 0.00420 -0.1181 0.7154 0.0089
-6.000 -0.1154 0.01022 0.00396 -0.1179 0.6972 0.0099
-5.750 -0.0894 0.01009 0.00375 -0.1178 0.6796 0.0110
-5.500 -0.0631 0.00999 0.00356 -0.1176 0.6616 0.0119
-5.250 -0.0366 0.00987 0.00336 -0.1176 0.6450 0.0132
-5.000 -0.0095 0.00974 0.00318 -0.1177 0.6313 0.0150
-4.750 0.0180 0.00963 0.00301 -0.1178 0.6198 0.0165
-4.500 0.0456 0.00949 0.00283 -0.1179 0.6082 0.0202
-4.250 0.0736 0.00938 0.00268 -0.1181 0.5969 0.0245
-4.000 0.1019 0.00923 0.00253 -0.1185 0.5865 0.0339
-3.750 0.1303 0.00909 0.00239 -0.1188 0.5772 0.0485
-3.500 0.1591 0.00893 0.00226 -0.1192 0.5681 0.0689
-3.250 0.1886 0.00866 0.00210 -0.1200 0.5600 0.1178
-3.000 0.2192 0.00826 0.00192 -0.1212 0.5510 0.2015
-2.750 0.2527 0.00759 0.00170 -0.1233 0.5425 0.3499
-2.500 0.2865 0.00705 0.00156 -0.1254 0.5340 0.4931
-2.250 0.3170 0.00693 0.00154 -0.1261 0.5257 0.5441
-2.000 0.3464 0.00692 0.00156 -0.1266 0.5174 0.5766
-1.750 0.3754 0.00696 0.00159 -0.1268 0.5095 0.5958
-1.500 0.4040 0.00701 0.00161 -0.1270 0.5029 0.6057
-1.250 0.4328 0.00707 0.00162 -0.1273 0.4962 0.6136
-1.000 0.4612 0.00714 0.00165 -0.1274 0.4896 0.6194
-0.750 0.4900 0.00719 0.00167 -0.1276 0.4841 0.6247
-0.500 0.5186 0.00726 0.00170 -0.1278 0.4784 0.6289
-0.250 0.5470 0.00733 0.00175 -0.1280 0.4734 0.6330
0.000 0.5756 0.00739 0.00178 -0.1282 0.4679 0.6373
0.250 0.6039 0.00748 0.00182 -0.1283 0.4620 0.6414
0.500 0.6322 0.00755 0.00188 -0.1285 0.4565 0.6446
0.750 0.6605 0.00763 0.00194 -0.1286 0.4499 0.6479
1.000 0.6884 0.00772 0.00200 -0.1287 0.4436 0.6511
1.250 0.7167 0.00781 0.00205 -0.1288 0.4373 0.6542
1.500 0.7446 0.00791 0.00212 -0.1289 0.4313 0.6569
1.750 0.7727 0.00798 0.00219 -0.1291 0.4264 0.6593
2.000 0.8007 0.00807 0.00228 -0.1292 0.4210 0.6618
2.250 0.8283 0.00819 0.00237 -0.1292 0.4155 0.6646
2.500 0.8564 0.00827 0.00246 -0.1293 0.4105 0.6673
2.750 0.8842 0.00837 0.00254 -0.1294 0.4052 0.6699
3.000 0.9116 0.00849 0.00265 -0.1294 0.4004 0.6721
3.250 0.9395 0.00857 0.00275 -0.1295 0.3960 0.6740
3.500 0.9670 0.00868 0.00286 -0.1296 0.3905 0.6761
3.750 0.9942 0.00881 0.00299 -0.1296 0.3849 0.6783
4.000 1.0217 0.00891 0.00311 -0.1296 0.3793 0.6804
4.250 1.0488 0.00904 0.00324 -0.1296 0.3737 0.6825
4.500 1.0759 0.00917 0.00337 -0.1296 0.3688 0.6845
4.750 1.1029 0.00931 0.00351 -0.1295 0.3619 0.6864
5.000 1.1292 0.00947 0.00367 -0.1294 0.3532 0.6882
5.250 1.1549 0.00969 0.00385 -0.1291 0.3409 0.6899
5.500 1.1802 0.00993 0.00406 -0.1288 0.3255 0.6918
5.750 1.2051 0.01019 0.00427 -0.1284 0.3091 0.6938
6.000 1.2290 0.01053 0.00453 -0.1279 0.2890 0.6957
6.250 1.2517 0.01096 0.00483 -0.1272 0.2643 0.6975
6.500 1.2720 0.01155 0.00524 -0.1261 0.2302 0.6994
6.750 1.2913 0.01220 0.00571 -0.1248 0.1961 0.7011
7.000 1.3053 0.01321 0.00640 -0.1227 0.1437 0.7028
7.250 1.3211 0.01403 0.00705 -0.1209 0.1078 0.7045
7.500 1.3359 0.01488 0.00772 -0.1189 0.0761 0.7063
7.750 1.3518 0.01561 0.00834 -0.1170 0.0544 0.7081
8.000 1.3680 0.01623 0.00890 -0.1152 0.0392 0.7100
8.250 1.3803 0.01691 0.00951 -0.1127 0.0258 0.7119
8.500 1.3950 0.01748 0.01006 -0.1106 0.0191 0.7137
8.750 1.4094 0.01805 0.01063 -0.1085 0.0143 0.7152
9.000 1.4226 0.01869 0.01126 -0.1063 0.0095 0.7168
9.250 1.4307 0.01959 0.01217 -0.1033 0.0029 0.7186
9.500 1.4433 0.02027 0.01290 -0.1011 0.0023 0.7204
9.750 1.4568 0.02091 0.01360 -0.0991 0.0021 0.7221
10.000 1.4693 0.02161 0.01436 -0.0970 0.0019 0.7237
10.250 1.4808 0.02238 0.01520 -0.0950 0.0018 0.7254
10.500 1.4913 0.02324 0.01613 -0.0929 0.0017 0.7273
10.750 1.5007 0.02420 0.01715 -0.0907 0.0016 0.7291
11.000 1.5089 0.02527 0.01829 -0.0886 0.0015 0.7308
11.250 1.5159 0.02648 0.01959 -0.0866 0.0014 0.7324
11.500 1.5217 0.02785 0.02105 -0.0846 0.0014 0.7341
11.750 1.5258 0.02942 0.02272 -0.0826 0.0013 0.7357
12.000 1.5293 0.03114 0.02453 -0.0809 0.0012 0.7374
12.250 1.5345 0.03284 0.02631 -0.0795 0.0012 0.7392
12.500 1.5386 0.03472 0.02828 -0.0782 0.0012 0.7411
12.750 1.5419 0.03680 0.03044 -0.0772 0.0012 0.7430
13.000 1.5443 0.03907 0.03280 -0.0763 0.0012 0.7448
13.250 1.5461 0.04153 0.03535 -0.0757 0.0011 0.7465
13.500 1.5469 0.04422 0.03815 -0.0752 0.0011 0.7481
13.750 1.5470 0.04711 0.04114 -0.0750 0.0011 0.7498
14.000 1.5462 0.05023 0.04437 -0.0749 0.0010 0.7515
14.250 1.5446 0.05357 0.04782 -0.0750 0.0010 0.7532
14.500 1.5425 0.05708 0.05143 -0.0753 0.0010 0.7549
14.750 1.5395 0.06081 0.05527 -0.0758 0.0010 0.7567
15.000 1.5361 0.06474 0.05930 -0.0765 0.0009 0.7585
15.250 1.5320 0.06883 0.06350 -0.0773 0.0009 0.7601
15.500 1.5274 0.07313 0.06791 -0.0784 0.0009 0.7617
15.750 1.5225 0.07761 0.07250 -0.0796 0.0009 0.7634
16.000 1.5173 0.08224 0.07724 -0.0809 0.0008 0.7650
16.250 1.5121 0.08694 0.08206 -0.0824 0.0008 0.7666
16.500 1.5059 0.09192 0.08715 -0.0841 0.0008 0.7682
16.750 1.5000 0.09694 0.09227 -0.0859 0.0008 0.7698
17.000 1.4945 0.10197 0.09741 -0.0878 0.0008 0.7714
17.250 1.4874 0.10733 0.10289 -0.0900 0.0008 0.7729
17.500 1.4809 0.11267 0.10832 -0.0922 0.0008 0.7744
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