FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 500,000 Max Cl/Cd: 72.1 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63145-il-500000-n5.txt Download as CSV file: xf-fx63145-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1572 0.10100 0.09521 -0.0817 0.1648 0.0111
-10.750 -0.1536 0.09743 0.09165 -0.0832 0.1646 0.0112
-7.750 -0.2324 0.04066 0.03456 -0.1134 0.1629 0.0140
-6.750 -0.1769 0.02682 0.01932 -0.1140 0.1333 0.0093
-6.500 -0.1544 0.02476 0.01701 -0.1142 0.1302 0.0088
-6.250 -0.1302 0.02197 0.01373 -0.1139 0.1280 0.0076
-6.000 -0.1034 0.02118 0.01273 -0.1138 0.1264 0.0072
-5.750 -0.0766 0.02060 0.01200 -0.1138 0.1246 0.0071
-5.500 -0.0512 0.01919 0.01047 -0.1137 0.1238 0.0069
-5.250 -0.0247 0.01825 0.00941 -0.1137 0.1229 0.0068
-5.000 0.0023 0.01745 0.00852 -0.1137 0.1217 0.0067
-4.750 0.0297 0.01677 0.00775 -0.1138 0.1206 0.0067
-4.500 0.0576 0.01617 0.00707 -0.1140 0.1188 0.0066
-4.250 0.0861 0.01564 0.00646 -0.1144 0.1169 0.0066
-4.000 0.1150 0.01519 0.00594 -0.1149 0.1147 0.0065
-3.750 0.1445 0.01478 0.00545 -0.1154 0.1134 0.0065
-3.500 0.1742 0.01442 0.00503 -0.1159 0.1115 0.0066
-3.250 0.2037 0.01416 0.00468 -0.1164 0.0976 0.0066
-3.000 0.2331 0.01396 0.00438 -0.1168 0.0966 0.0067
-2.750 0.2624 0.01382 0.00415 -0.1172 0.0955 0.0068
-2.500 0.2916 0.01371 0.00395 -0.1175 0.0937 0.0069
-2.250 0.3207 0.01363 0.00379 -0.1178 0.0921 0.0071
-1.750 0.3787 0.01353 0.00357 -0.1183 0.0898 0.0087
-1.500 0.4076 0.01350 0.00353 -0.1185 0.0891 0.0168
-1.250 0.4362 0.01351 0.00354 -0.1187 0.0886 0.0354
-1.000 0.4645 0.01356 0.00355 -0.1188 0.0883 0.0379
-0.750 0.4928 0.01361 0.00357 -0.1189 0.0880 0.0397
-0.500 0.5212 0.01364 0.00359 -0.1191 0.0877 0.0441
-0.250 0.5497 0.01367 0.00362 -0.1193 0.0874 0.0517
0.000 0.5777 0.01375 0.00370 -0.1193 0.0872 0.0675
0.250 0.6059 0.01381 0.00379 -0.1195 0.0869 0.0980
0.500 0.6340 0.01388 0.00385 -0.1196 0.0867 0.1046
0.750 0.6616 0.01400 0.00395 -0.1196 0.0864 0.1054
1.000 0.6891 0.01412 0.00407 -0.1196 0.0862 0.1062
1.250 0.7165 0.01425 0.00419 -0.1196 0.0860 0.1072
1.500 0.7438 0.01439 0.00432 -0.1195 0.0858 0.1086
1.750 0.7711 0.01452 0.00447 -0.1195 0.0856 0.1132
2.000 0.7987 0.01462 0.00463 -0.1196 0.0854 0.1236
2.250 0.8254 0.01481 0.00481 -0.1195 0.0850 0.1391
2.500 0.8521 0.01499 0.00501 -0.1194 0.0845 0.1449
2.750 0.8785 0.01519 0.00521 -0.1192 0.0841 0.1489
3.000 0.9050 0.01537 0.00542 -0.1191 0.0838 0.1549
3.250 0.9319 0.01553 0.00567 -0.1191 0.0835 0.1843
3.500 0.9579 0.01575 0.00591 -0.1189 0.0832 0.1978
3.750 0.9845 0.01592 0.00616 -0.1189 0.0829 0.2175
4.000 1.0120 0.01602 0.00645 -0.1193 0.0826 0.3122
4.250 1.0407 0.01603 0.00679 -0.1200 0.0823 0.4352
4.500 1.0677 0.01615 0.00706 -0.1201 0.0821 0.4812
4.750 1.0935 0.01636 0.00732 -0.1199 0.0820 0.5011
5.250 1.1450 0.01677 0.00790 -0.1196 0.0817 0.5403
5.500 1.1700 0.01701 0.00819 -0.1192 0.0815 0.5558
5.750 1.1947 0.01726 0.00849 -0.1188 0.0813 0.5660
6.000 1.2197 0.01749 0.00878 -0.1185 0.0808 0.5773
6.250 1.2455 0.01763 0.00898 -0.1183 0.0786 0.5899
6.500 1.2702 0.01784 0.00926 -0.1180 0.0761 0.6022
6.750 1.2940 0.01812 0.00959 -0.1175 0.0748 0.6120
7.000 1.3184 0.01834 0.00985 -0.1170 0.0736 0.6198
7.250 1.3418 0.01861 0.01017 -0.1165 0.0601 0.6274
7.500 1.3616 0.01912 0.01056 -0.1154 0.0531 0.6338
7.750 1.3792 0.01974 0.01126 -0.1140 0.0488 0.6400
8.000 1.3970 0.02031 0.01188 -0.1126 0.0459 0.6466
8.250 1.4166 0.02068 0.01233 -0.1115 0.0436 0.6547
8.500 1.4227 0.02166 0.01322 -0.1083 0.0207 0.6644
8.750 1.4318 0.02250 0.01407 -0.1056 0.0124 0.6764
9.000 1.4426 0.02326 0.01489 -0.1034 0.0091 0.6877
9.250 1.4496 0.02426 0.01594 -0.1007 0.0028 0.6994
9.500 1.4598 0.02512 0.01692 -0.0986 0.0025 0.7132
9.750 1.4691 0.02608 0.01802 -0.0966 0.0024 0.7331
10.000 1.4775 0.02716 0.01922 -0.0947 0.0023 0.7523
10.250 1.4847 0.02837 0.02059 -0.0929 0.0022 0.7735
10.500 1.4907 0.02972 0.02211 -0.0912 0.0021 0.8051
10.750 1.4944 0.03116 0.02377 -0.0893 0.0020 0.8603
11.000 1.4924 0.03270 0.02551 -0.0867 0.0020 1.0000
11.250 1.4969 0.03471 0.02762 -0.0859 0.0020 1.0000
11.500 1.5007 0.03692 0.02993 -0.0852 0.0019 1.0000
11.750 1.5038 0.03931 0.03241 -0.0848 0.0019 1.0000
12.000 1.5065 0.04184 0.03505 -0.0845 0.0019 1.0000
12.250 1.5086 0.04453 0.03783 -0.0843 0.0019 1.0000
12.500 1.5098 0.04738 0.04078 -0.0842 0.0018 1.0000
12.750 1.5103 0.05039 0.04390 -0.0843 0.0018 1.0000
13.000 1.5098 0.05358 0.04720 -0.0845 0.0018 1.0000
13.250 1.5084 0.05696 0.05068 -0.0848 0.0017 1.0000
13.500 1.5066 0.06050 0.05433 -0.0852 0.0017 1.0000
13.750 1.5041 0.06418 0.05813 -0.0857 0.0016 1.0000
14.000 1.5012 0.06805 0.06212 -0.0864 0.0016 1.0000
14.250 1.4977 0.07213 0.06631 -0.0873 0.0015 1.0000
14.500 1.4940 0.07636 0.07065 -0.0883 0.0015 1.0000
14.750 1.4899 0.08075 0.07516 -0.0895 0.0015 1.0000
15.000 1.4850 0.08539 0.07992 -0.0909 0.0014 1.0000
15.250 1.4800 0.09015 0.08480 -0.0924 0.0014 1.0000
15.500 1.4742 0.09516 0.08993 -0.0941 0.0014 1.0000
15.750 1.4676 0.10042 0.09532 -0.0960 0.0014 1.0000
16.000 1.4609 0.10580 0.10082 -0.0980 0.0014 1.0000
16.250 1.4541 0.11126 0.10641 -0.1002 0.0013 1.0000
16.500 1.4467 0.11692 0.11219 -0.1026 0.0013 1.0000
16.750 1.4387 0.12280 0.11819 -0.1052 0.0013 1.0000
17.000 1.4318 0.12853 0.12403 -0.1079 0.0013 1.0000
17.250 1.4234 0.13459 0.13021 -0.1109 0.0013 1.0000
17.500 1.4149 0.14075 0.13649 -0.1140 0.0012 1.0000
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