FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 50,000 Max Cl/Cd: 40 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63120-il-50000-n5.txt Download as CSV file: xf-fx63120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-120 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3091 0.11397 0.10743 -0.0356 1.0000 0.1316
-8.500 -0.3329 0.11376 0.10739 -0.0344 1.0000 0.1338
-8.250 -0.3627 0.10573 0.09940 -0.0377 1.0000 0.0743
-8.000 -0.3665 0.10364 0.09738 -0.0354 1.0000 0.0738
-7.750 -0.3690 0.10128 0.09508 -0.0340 0.9991 0.0731
-7.500 -0.3555 0.09720 0.09099 -0.0375 0.9927 0.0719
-7.250 -0.3444 0.09298 0.08678 -0.0415 0.9855 0.0701
-7.000 -0.3350 0.08812 0.08192 -0.0468 0.9771 0.0682
-6.750 -0.3256 0.08218 0.07599 -0.0541 0.9677 0.0663
-6.500 -0.3134 0.07477 0.06854 -0.0644 0.9580 0.0653
-6.250 -0.2952 0.06628 0.05987 -0.0776 0.9492 0.0654
-6.000 -0.2687 0.05885 0.05209 -0.0896 0.9419 0.0662
-5.750 -0.2359 0.05197 0.04468 -0.1004 0.9354 0.0663
-5.500 -0.1953 0.04653 0.03862 -0.1093 0.9302 0.0671
-5.250 -0.1490 0.04249 0.03389 -0.1169 0.9268 0.0706
-5.000 -0.1092 0.03939 0.03012 -0.1218 0.9217 0.0728
-4.750 -0.0694 0.03701 0.02711 -0.1255 0.9166 0.0744
-4.500 -0.0322 0.03522 0.02522 -0.1283 0.9126 0.0783
-4.250 0.0027 0.03393 0.02371 -0.1303 0.9077 0.0825
-4.000 0.0337 0.03282 0.02234 -0.1311 0.9014 0.0855
-3.750 0.0699 0.03179 0.02106 -0.1326 0.8969 0.0895
-3.500 0.1031 0.03095 0.02024 -0.1340 0.8920 0.0968
-3.250 0.1316 0.03040 0.01951 -0.1343 0.8848 0.1035
-3.000 0.1707 0.02955 0.01869 -0.1368 0.8803 0.1140
-2.750 0.2159 0.02860 0.01780 -0.1408 0.8765 0.1400
-2.500 0.2572 0.02736 0.01727 -0.1451 0.8699 0.2475
-2.250 0.2945 0.02726 0.01779 -0.1467 0.8644 0.4576
-2.000 0.3230 0.02764 0.01827 -0.1459 0.8581 0.5262
-1.750 0.3414 0.02822 0.01894 -0.1430 0.8492 0.5784
-1.500 0.3715 0.02839 0.01907 -0.1420 0.8443 0.6177
-1.250 0.3916 0.02867 0.01925 -0.1406 0.8341 0.6362
-1.000 0.4289 0.02855 0.01896 -0.1419 0.8290 0.6554
-0.750 0.4526 0.02873 0.01905 -0.1412 0.8198 0.6709
-0.500 0.4871 0.02864 0.01885 -0.1422 0.8137 0.6871
-0.250 0.5157 0.02871 0.01883 -0.1423 0.8059 0.7016
0.000 0.5459 0.02872 0.01876 -0.1427 0.7984 0.7170
0.250 0.5806 0.02857 0.01854 -0.1436 0.7927 0.7334
0.500 0.6031 0.02881 0.01876 -0.1429 0.7829 0.7497
1.000 0.6581 0.02890 0.01881 -0.1426 0.7671 0.7878
1.500 0.7062 0.02891 0.01887 -0.1408 0.7508 0.8319
2.000 0.7480 0.02878 0.01885 -0.1377 0.7339 0.9013
2.250 0.7787 0.02877 0.01885 -0.1383 0.7255 1.0000
2.500 0.8155 0.02903 0.01904 -0.1404 0.7169 1.0000
2.750 0.8484 0.02940 0.01938 -0.1417 0.7077 1.0000
3.000 0.8855 0.02950 0.01944 -0.1433 0.6998 1.0000
3.250 0.9128 0.03002 0.01996 -0.1437 0.6891 1.0000
3.500 0.9523 0.02988 0.01981 -0.1453 0.6822 1.0000
3.750 0.9757 0.03049 0.02044 -0.1450 0.6702 1.0000
4.000 1.0099 0.03053 0.02051 -0.1457 0.6615 1.0000
4.500 1.0637 0.03116 0.02121 -0.1453 0.6384 1.0000
4.750 1.0947 0.03118 0.02129 -0.1454 0.6276 1.0000
5.000 1.1281 0.03104 0.02118 -0.1457 0.6169 1.0000
5.250 1.1499 0.03152 0.02174 -0.1447 0.6034 1.0000
5.500 1.1739 0.03188 0.02220 -0.1440 0.5905 1.0000
5.750 1.2013 0.03206 0.02245 -0.1436 0.5784 1.0000
6.000 1.2336 0.03193 0.02238 -0.1436 0.5668 1.0000
6.250 1.2555 0.03238 0.02295 -0.1426 0.5529 1.0000
6.500 1.2766 0.03286 0.02353 -0.1414 0.5385 1.0000
6.750 1.2984 0.03328 0.02406 -0.1403 0.5239 1.0000
7.000 1.3203 0.03368 0.02458 -0.1391 0.5088 1.0000
7.250 1.3419 0.03407 0.02505 -0.1378 0.4930 1.0000
7.500 1.3630 0.03440 0.02544 -0.1364 0.4756 1.0000
7.750 1.3844 0.03461 0.02564 -0.1349 0.4561 1.0000
8.000 1.3949 0.03539 0.02648 -0.1322 0.4354 1.0000
8.250 1.4053 0.03621 0.02734 -0.1296 0.4145 1.0000
8.500 1.4167 0.03706 0.02821 -0.1273 0.3942 1.0000
8.750 1.4277 0.03803 0.02917 -0.1250 0.3747 1.0000
9.000 1.4330 0.03943 0.03066 -0.1224 0.3552 1.0000
9.250 1.4386 0.04089 0.03222 -0.1200 0.3358 1.0000
9.500 1.4437 0.04245 0.03381 -0.1177 0.3163 1.0000
9.750 1.4481 0.04413 0.03547 -0.1155 0.2973 1.0000
10.000 1.4510 0.04607 0.03742 -0.1134 0.2787 1.0000
10.250 1.4526 0.04825 0.03963 -0.1115 0.2602 1.0000
10.500 1.4534 0.05062 0.04200 -0.1097 0.2424 1.0000
10.750 1.4535 0.05318 0.04457 -0.1082 0.2256 1.0000
11.000 1.4535 0.05589 0.04728 -0.1068 0.2100 1.0000
11.250 1.4531 0.05876 0.05016 -0.1056 0.1955 1.0000
11.500 1.4528 0.06172 0.05315 -0.1046 0.1824 1.0000
11.750 1.4531 0.06473 0.05616 -0.1037 0.1710 1.0000
12.000 1.4535 0.06779 0.05927 -0.1030 0.1606 1.0000
12.250 1.4547 0.07097 0.06260 -0.1024 0.1509 1.0000
12.500 1.4567 0.07400 0.06565 -0.1019 0.1429 1.0000
12.750 1.4583 0.07726 0.06908 -0.1015 0.1351 1.0000
13.000 1.4625 0.08019 0.07205 -0.1011 0.1288 1.0000
13.250 1.4644 0.08359 0.07567 -0.1009 0.1225 1.0000
13.500 1.4705 0.08623 0.07826 -0.1005 0.1170 1.0000
13.750 1.4685 0.09042 0.08279 -0.1009 0.1118 1.0000
14.000 1.4719 0.09364 0.08612 -0.1009 0.1071 1.0000
14.250 1.4789 0.09649 0.08907 -0.1007 0.1030 1.0000
14.500 1.4720 0.10164 0.09457 -0.1018 0.0995 1.0000
14.750 1.4681 0.10625 0.09940 -0.1030 0.0961 1.0000
15.000 1.4834 0.10750 0.10053 -0.1022 0.0917 1.0000
15.250 1.4671 0.11445 0.10786 -0.1050 0.0898 1.0000
15.500 1.4478 0.12231 0.11608 -0.1087 0.0881 1.0000
15.750 1.4253 0.13125 0.12533 -0.1135 0.0868 1.0000
16.000 1.3941 0.14286 0.13723 -0.1207 0.0862 1.0000
16.250 1.3292 0.16540 0.15998 -0.1361 0.0870 1.0000
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Polar data table (+)
Polar graphs
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