WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il) Reynolds number: 100,000 Max Cl/Cd: 62.09 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137-il-100000.txt Download as CSV file: xf-fx63137-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 63-137 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2422 0.10601 0.10184 -0.0571 0.9619 0.1126
-7.500 -0.2151 0.10132 0.09713 -0.0582 0.9592 0.1177
-7.250 -0.2169 0.09922 0.09506 -0.0597 0.9504 0.1245
-7.000 -0.1999 0.09557 0.09141 -0.0621 0.9459 0.1326
-6.750 -0.2156 0.09427 0.09017 -0.0629 0.9355 0.1392
-6.500 -0.1983 0.09123 0.08712 -0.0645 0.9308 0.1528
-6.000 -0.2137 0.08432 0.08029 -0.0802 0.9077 0.1708
-5.750 -0.1802 0.08369 0.07962 -0.0671 0.9067 0.1806
-5.500 -0.1712 0.07792 0.07382 -0.0861 0.8972 0.2017
-5.250 -0.1757 0.07657 0.07253 -0.0789 0.8890 0.2032
-5.000 -0.0587 0.04293 0.03660 -0.1398 0.8877 0.0991
-4.750 -0.0091 0.03927 0.03252 -0.1460 0.8847 0.0955
-4.500 0.0460 0.03648 0.02915 -0.1525 0.8824 0.0946
-4.250 0.1005 0.03422 0.02640 -0.1579 0.8804 0.0935
-4.000 0.1218 0.03356 0.02552 -0.1576 0.8722 0.0935
-3.750 0.1649 0.03227 0.02401 -0.1603 0.8677 0.0949
-3.500 0.2143 0.03094 0.02249 -0.1637 0.8646 0.0981
-3.250 0.2388 0.03051 0.02201 -0.1633 0.8562 0.1014
-3.000 0.2789 0.02951 0.02116 -0.1653 0.8513 0.1102
-2.750 0.3310 0.02824 0.02009 -0.1696 0.8485 0.1347
-2.500 0.4042 0.02612 0.01941 -0.1791 0.8475 0.4397
-2.250 0.4152 0.02723 0.02053 -0.1761 0.8370 0.4923
-2.000 0.4484 0.02763 0.02091 -0.1757 0.8326 0.5365
-1.750 0.4874 0.02774 0.02099 -0.1759 0.8302 0.5713
-1.500 0.4896 0.02884 0.02211 -0.1716 0.8179 0.5883
-1.250 0.5302 0.02859 0.02181 -0.1720 0.8148 0.6160
-1.000 0.5397 0.02932 0.02256 -0.1685 0.8038 0.6335
-0.750 0.5722 0.02910 0.02233 -0.1674 0.7995 0.6575
-0.500 0.6183 0.02856 0.02169 -0.1693 0.7972 0.6808
-0.250 0.6210 0.02938 0.02255 -0.1652 0.7850 0.6905
0.000 0.6672 0.02874 0.02181 -0.1676 0.7820 0.7049
0.250 0.7158 0.02806 0.02103 -0.1705 0.7798 0.7185
0.500 0.7199 0.02905 0.02206 -0.1671 0.7673 0.7286
0.750 0.7642 0.02835 0.02130 -0.1691 0.7644 0.7418
1.000 0.7798 0.02906 0.02201 -0.1678 0.7533 0.7520
1.250 0.8227 0.02837 0.02127 -0.1696 0.7493 0.7634
1.500 0.8690 0.02751 0.02035 -0.1718 0.7464 0.7750
1.750 0.8826 0.02823 0.02110 -0.1701 0.7343 0.7858
2.000 0.9291 0.02730 0.02011 -0.1722 0.7307 0.7993
2.250 0.9407 0.02785 0.02073 -0.1697 0.7191 0.8102
2.500 0.9850 0.02693 0.01977 -0.1715 0.7146 0.8232
2.750 1.0034 0.02734 0.02021 -0.1702 0.7038 0.8357
3.250 1.0594 0.02706 0.01998 -0.1697 0.6888 0.8631
3.500 1.0933 0.02648 0.01940 -0.1700 0.6826 0.8793
3.750 1.1115 0.02662 0.01960 -0.1683 0.6734 0.8982
4.000 1.1373 0.02597 0.01898 -0.1671 0.6662 0.9236
4.250 1.1593 0.02585 0.01893 -0.1660 0.6560 1.0000
4.500 1.2160 0.02499 0.01798 -0.1708 0.6479 1.0000
4.750 1.2503 0.02520 0.01822 -0.1725 0.6357 1.0000
5.000 1.2948 0.02485 0.01782 -0.1755 0.6258 1.0000
5.250 1.3362 0.02457 0.01750 -0.1778 0.6153 1.0000
5.500 1.3658 0.02479 0.01774 -0.1784 0.6030 1.0000
5.750 1.4006 0.02464 0.01754 -0.1794 0.5911 1.0000
6.000 1.4384 0.02428 0.01707 -0.1807 0.5791 1.0000
6.250 1.4621 0.02445 0.01726 -0.1800 0.5649 1.0000
6.500 1.4863 0.02461 0.01745 -0.1793 0.5510 1.0000
6.750 1.5109 0.02479 0.01762 -0.1786 0.5370 1.0000
7.000 1.5352 0.02500 0.01782 -0.1778 0.5230 1.0000
7.250 1.5590 0.02526 0.01807 -0.1770 0.5092 1.0000
7.500 1.5840 0.02551 0.01829 -0.1764 0.4961 1.0000
7.750 1.6024 0.02596 0.01879 -0.1748 0.4819 1.0000
8.000 1.6198 0.02646 0.01933 -0.1730 0.4670 1.0000
8.250 1.6351 0.02702 0.01994 -0.1709 0.4516 1.0000
8.500 1.6490 0.02761 0.02057 -0.1687 0.4364 1.0000
8.750 1.6619 0.02821 0.02118 -0.1662 0.4209 1.0000
9.000 1.6718 0.02890 0.02189 -0.1633 0.4054 1.0000
9.250 1.6780 0.02974 0.02276 -0.1600 0.3894 1.0000
9.500 1.6810 0.03072 0.02378 -0.1563 0.3728 1.0000
9.750 1.6839 0.03180 0.02487 -0.1528 0.3563 1.0000
10.000 1.6858 0.03307 0.02614 -0.1494 0.3394 1.0000
10.250 1.6849 0.03460 0.02772 -0.1460 0.3213 1.0000
10.500 1.6822 0.03634 0.02945 -0.1426 0.3029 1.0000
10.750 1.6786 0.03835 0.03135 -0.1394 0.2845 1.0000
11.000 1.6714 0.04084 0.03390 -0.1363 0.2628 1.0000
11.250 1.6626 0.04365 0.03661 -0.1335 0.2419 1.0000
11.500 1.6536 0.04678 0.03955 -0.1309 0.2222 1.0000
11.750 1.6444 0.05022 0.04298 -0.1287 0.2007 1.0000
12.000 1.6374 0.05360 0.04622 -0.1268 0.1846 1.0000
12.250 1.6362 0.05668 0.04916 -0.1252 0.1707 1.0000
12.500 1.6402 0.05937 0.05182 -0.1239 0.1594 1.0000
12.750 1.6473 0.06176 0.05412 -0.1228 0.1510 1.0000
13.000 1.6543 0.06416 0.05660 -0.1219 0.1441 1.0000
13.250 1.6719 0.06569 0.05801 -0.1211 0.1385 1.0000
13.500 1.6849 0.06775 0.06022 -0.1203 0.1340 1.0000
13.750 1.7046 0.06920 0.06165 -0.1197 0.1297 1.0000
14.000 1.7306 0.07045 0.06287 -0.1192 0.1252 1.0000
14.250 1.7322 0.07342 0.06614 -0.1184 0.1222 1.0000
14.500 1.7367 0.07606 0.06892 -0.1178 0.1184 1.0000
14.750 1.7613 0.07718 0.06985 -0.1175 0.1135 1.0000
15.000 1.7531 0.08093 0.07395 -0.1169 0.1114 1.0000
15.250 1.7482 0.08452 0.07781 -0.1165 0.1087 1.0000
15.500 1.7486 0.08752 0.08094 -0.1164 0.1058 1.0000
15.750 1.7681 0.08865 0.08192 -0.1161 0.1017 1.0000
16.000 1.7584 0.09294 0.08655 -0.1162 0.1002 1.0000
16.250 1.7494 0.09726 0.09116 -0.1166 0.0982 1.0000
16.500 1.7449 0.10115 0.09527 -0.1172 0.0962 1.0000
16.750 1.7491 0.10372 0.09788 -0.1175 0.0935 1.0000
17.000 1.7685 0.10485 0.09892 -0.1172 0.0903 1.0000
17.250 1.7530 0.11023 0.10466 -0.1186 0.0894 1.0000
17.500 1.7368 0.11597 0.11073 -0.1205 0.0883 1.0000
17.750 1.7212 0.12191 0.11697 -0.1229 0.0873 1.0000
18.000 1.7045 0.12826 0.12361 -0.1257 0.0866 1.0000
18.250 1.6843 0.13543 0.13107 -0.1294 0.0858 1.0000
18.500 1.6505 0.14570 0.14169 -0.1353 0.0862 1.0000
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