FX 63-120 AIRFOIL (fx63120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-120 AIRFOIL (fx63120-il) Reynolds number: 100,000 Max Cl/Cd: 64.71 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63120-il-100000.txt Download as CSV file: xf-fx63120-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2956 0.11667 0.11175 -0.0401 1.0000 0.0966
-9.500 -0.3205 0.11671 0.11194 -0.0407 1.0000 0.0985
-9.250 -0.3464 0.11680 0.11219 -0.0399 1.0000 0.0990
-9.000 -0.3415 0.11240 0.10784 -0.0374 1.0000 0.1002
-8.750 -0.3232 0.10907 0.10450 -0.0336 1.0000 0.1029
-8.500 -0.3274 0.10766 0.10314 -0.0309 1.0000 0.1053
-8.250 -0.3374 0.10655 0.10211 -0.0286 1.0000 0.1084
-8.000 -0.2946 0.10068 0.09674 -0.0304 0.9925 0.1164
-7.750 -0.2693 0.09700 0.09303 -0.0314 0.9881 0.1229
-7.500 -0.2830 0.09388 0.08996 -0.0376 0.9817 0.1289
-7.250 -0.2723 0.08886 0.08495 -0.0395 0.9765 0.1318
-7.000 -0.3797 0.09843 0.09434 -0.0229 0.9962 0.1218
-6.500 -0.3628 0.09099 0.08695 -0.0342 0.9812 0.1333
-6.250 -0.3503 0.08398 0.07992 -0.0569 0.9683 0.1461
-6.000 -0.3325 0.08287 0.07882 -0.0461 0.9657 0.1486
-5.750 -0.3119 0.07681 0.07272 -0.0607 0.9565 0.1630
-5.500 -0.2947 0.07625 0.07218 -0.0525 0.9523 0.1676
-5.250 -0.2658 0.07037 0.06619 -0.0697 0.9433 0.1934
-5.000 -0.2522 0.06870 0.06459 -0.0638 0.9380 0.1985
-4.750 -0.1121 0.03772 0.03106 -0.1218 0.9389 0.0956
-4.500 -0.0591 0.03427 0.02702 -0.1283 0.9361 0.0943
-4.250 -0.0053 0.03152 0.02370 -0.1339 0.9338 0.0927
-4.000 0.0278 0.03024 0.02207 -0.1355 0.9269 0.0952
-3.750 0.0722 0.02897 0.02044 -0.1386 0.9224 0.0980
-3.500 0.1192 0.02743 0.01876 -0.1420 0.9194 0.1010
-3.250 0.1464 0.02676 0.01816 -0.1424 0.9113 0.1066
-3.000 0.1895 0.02593 0.01728 -0.1449 0.9065 0.1150
-2.750 0.2349 0.02499 0.01647 -0.1481 0.9025 0.1289
-2.500 0.2707 0.02419 0.01594 -0.1502 0.8946 0.1650
-2.250 0.3240 0.02312 0.01615 -0.1551 0.8909 0.5037
-2.000 0.3543 0.02356 0.01662 -0.1548 0.8840 0.5499
-1.750 0.3797 0.02407 0.01718 -0.1533 0.8759 0.5910
-1.500 0.4153 0.02424 0.01742 -0.1529 0.8720 0.6283
-1.250 0.4285 0.02482 0.01802 -0.1499 0.8610 0.6509
-1.000 0.4695 0.02460 0.01774 -0.1512 0.8570 0.6737
-0.750 0.4953 0.02480 0.01789 -0.1510 0.8481 0.6881
-0.500 0.5336 0.02453 0.01758 -0.1523 0.8427 0.7024
-0.250 0.5799 0.02402 0.01701 -0.1549 0.8395 0.7183
0.000 0.5981 0.02434 0.01735 -0.1533 0.8284 0.7306
0.250 0.6415 0.02382 0.01679 -0.1555 0.8243 0.7459
0.500 0.6648 0.02400 0.01698 -0.1547 0.8144 0.7606
0.750 0.7033 0.02355 0.01652 -0.1560 0.8089 0.7786
1.000 0.7300 0.02355 0.01654 -0.1556 0.8001 0.7971
1.250 0.7621 0.02319 0.01619 -0.1557 0.7931 0.8177
1.500 0.7847 0.02311 0.01615 -0.1542 0.7843 0.8400
1.750 0.8112 0.02274 0.01581 -0.1531 0.7766 0.8655
2.000 0.8278 0.02268 0.01581 -0.1506 0.7667 0.8944
2.250 0.8507 0.02206 0.01524 -0.1486 0.7595 0.9361
2.500 0.8860 0.02208 0.01527 -0.1504 0.7486 1.0000
2.750 0.9377 0.02161 0.01474 -0.1545 0.7422 1.0000
3.000 0.9726 0.02181 0.01493 -0.1562 0.7301 1.0000
3.250 1.0131 0.02160 0.01467 -0.1582 0.7201 1.0000
3.500 1.0537 0.02124 0.01426 -0.1599 0.7099 1.0000
3.750 1.0842 0.02135 0.01437 -0.1603 0.6968 1.0000
4.000 1.1162 0.02139 0.01440 -0.1608 0.6848 1.0000
4.250 1.1536 0.02115 0.01411 -0.1619 0.6750 1.0000
4.500 1.1826 0.02126 0.01424 -0.1619 0.6619 1.0000
4.750 1.2100 0.02145 0.01445 -0.1616 0.6486 1.0000
5.000 1.2385 0.02156 0.01460 -0.1614 0.6354 1.0000
5.250 1.2680 0.02163 0.01467 -0.1613 0.6225 1.0000
5.500 1.2978 0.02164 0.01467 -0.1612 0.6091 1.0000
5.750 1.3261 0.02168 0.01471 -0.1608 0.5942 1.0000
6.000 1.3505 0.02174 0.01479 -0.1597 0.5761 1.0000
6.250 1.3741 0.02177 0.01483 -0.1585 0.5563 1.0000
6.500 1.3983 0.02184 0.01489 -0.1574 0.5365 1.0000
6.750 1.4227 0.02202 0.01503 -0.1564 0.5176 1.0000
7.000 1.4449 0.02233 0.01534 -0.1551 0.4978 1.0000
7.250 1.4649 0.02274 0.01579 -0.1535 0.4760 1.0000
7.500 1.4856 0.02317 0.01616 -0.1520 0.4541 1.0000
7.750 1.5025 0.02374 0.01673 -0.1500 0.4296 1.0000
8.000 1.5188 0.02436 0.01722 -0.1479 0.4043 1.0000
8.250 1.5302 0.02509 0.01800 -0.1451 0.3769 1.0000
8.500 1.5403 0.02592 0.01878 -0.1423 0.3496 1.0000
8.750 1.5481 0.02687 0.01965 -0.1391 0.3227 1.0000
9.000 1.5521 0.02799 0.02068 -0.1355 0.2958 1.0000
9.250 1.5529 0.02931 0.02191 -0.1315 0.2694 1.0000
9.500 1.5521 0.03092 0.02336 -0.1276 0.2446 1.0000
9.750 1.5508 0.03276 0.02508 -0.1240 0.2209 1.0000
10.000 1.5505 0.03480 0.02696 -0.1208 0.2000 1.0000
10.250 1.5516 0.03688 0.02898 -0.1179 0.1812 1.0000
10.500 1.5541 0.03900 0.03105 -0.1154 0.1655 1.0000
10.750 1.5579 0.04116 0.03316 -0.1132 0.1520 1.0000
11.000 1.5637 0.04334 0.03527 -0.1113 0.1404 1.0000
11.250 1.5735 0.04548 0.03727 -0.1098 0.1300 1.0000
11.500 1.5795 0.04766 0.03963 -0.1081 0.1212 1.0000
11.750 1.5915 0.04986 0.04181 -0.1068 0.1133 1.0000
12.000 1.6024 0.05196 0.04394 -0.1056 0.1065 1.0000
12.250 1.6156 0.05432 0.04638 -0.1045 0.1001 1.0000
12.500 1.6246 0.05660 0.04879 -0.1033 0.0947 1.0000
12.750 1.6434 0.05904 0.05121 -0.1026 0.0891 1.0000
13.000 1.6445 0.06187 0.05435 -0.1011 0.0853 1.0000
13.250 1.6567 0.06422 0.05670 -0.1003 0.0808 1.0000
13.500 1.6670 0.06754 0.06019 -0.0994 0.0771 1.0000
13.750 1.6605 0.07111 0.06412 -0.0980 0.0747 1.0000
14.000 1.6570 0.07458 0.06782 -0.0969 0.0720 1.0000
14.250 1.6840 0.07754 0.07061 -0.0969 0.0673 1.0000
14.500 1.6647 0.08194 0.07542 -0.0958 0.0666 1.0000
14.750 1.6459 0.08693 0.08079 -0.0953 0.0658 1.0000
15.000 1.6261 0.09236 0.08660 -0.0954 0.0650 1.0000
15.250 1.6046 0.09831 0.09289 -0.0963 0.0643 1.0000
15.500 1.5817 0.10477 0.09967 -0.0979 0.0638 1.0000
15.750 1.5568 0.11189 0.10711 -0.1005 0.0635 1.0000
16.000 1.5279 0.12027 0.11580 -0.1045 0.0637 1.0000
16.250 1.4956 0.12992 0.12575 -0.1100 0.0642 1.0000
16.500 1.4606 0.14110 0.13717 -0.1171 0.0651 1.0000
16.750 1.4238 0.15401 0.15028 -0.1260 0.0661 1.0000
17.000 1.3880 0.16824 0.16464 -0.1361 0.0671 1.0000
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