WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il) Reynolds number: 200,000 Max Cl/Cd: 90.58 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137-il-200000.txt Download as CSV file: xf-fx63137-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2059 0.12152 0.11814 -0.0557 0.9866 0.0431
-10.250 -0.1992 0.11617 0.11279 -0.0643 0.9835 0.0448
-10.000 -0.1931 0.11079 0.10744 -0.0702 0.9770 0.0452
-9.750 -0.1662 0.10774 0.10436 -0.0702 0.9747 0.0461
-9.500 -0.1450 0.10407 0.10069 -0.0738 0.9723 0.0478
-9.250 -0.1335 0.10011 0.09673 -0.0775 0.9655 0.0496
-9.000 -0.1372 0.09181 0.08845 -0.0918 0.9592 0.0517
-8.750 -0.1033 0.09038 0.08701 -0.0885 0.9585 0.0536
-8.500 -0.0925 0.08726 0.08389 -0.0911 0.9500 0.0572
-8.250 -0.0870 0.07999 0.07665 -0.1011 0.9452 0.0602
-8.000 -0.0651 0.07860 0.07524 -0.1010 0.9398 0.0658
-7.500 -0.0944 0.03637 0.03158 -0.1615 0.9131 0.0450
-7.250 -0.0802 0.03975 0.03565 -0.1538 0.9057 0.0490
-7.000 -0.0366 0.03204 0.02689 -0.1675 0.9015 0.0509
-6.750 0.0088 0.02842 0.02273 -0.1739 0.8993 0.0510
-6.500 0.0569 0.02565 0.01943 -0.1799 0.8974 0.0521
-6.250 0.0826 0.02455 0.01838 -0.1802 0.8900 0.0536
-6.000 0.1206 0.02328 0.01694 -0.1829 0.8855 0.0554
-5.750 0.1638 0.02189 0.01525 -0.1864 0.8822 0.0573
-5.500 0.2016 0.02067 0.01376 -0.1887 0.8780 0.0580
-5.250 0.2287 0.01978 0.01272 -0.1887 0.8709 0.0581
-5.000 0.2655 0.01879 0.01156 -0.1904 0.8665 0.0585
-4.750 0.3024 0.01789 0.01055 -0.1922 0.8622 0.0597
-4.500 0.3266 0.01726 0.00998 -0.1916 0.8544 0.0612
-4.250 0.3616 0.01658 0.00930 -0.1930 0.8493 0.0632
-4.000 0.3947 0.01605 0.00872 -0.1941 0.8439 0.0658
-3.750 0.4251 0.01549 0.00818 -0.1948 0.8369 0.0699
-3.500 0.4648 0.01478 0.00750 -0.1975 0.8319 0.0811
-3.250 0.5012 0.01421 0.00700 -0.1997 0.8262 0.1132
-3.000 0.5436 0.01307 0.00676 -0.2042 0.8198 0.3471
-2.750 0.5779 0.01301 0.00674 -0.2053 0.8143 0.4194
-2.500 0.6055 0.01314 0.00687 -0.2050 0.8071 0.4552
-2.250 0.6350 0.01326 0.00697 -0.2050 0.8003 0.4871
-2.000 0.6658 0.01342 0.00705 -0.2052 0.7948 0.5104
-1.750 0.6910 0.01362 0.00726 -0.2045 0.7874 0.5289
-1.500 0.7206 0.01377 0.00736 -0.2044 0.7816 0.5480
-1.250 0.7471 0.01397 0.00755 -0.2038 0.7749 0.5647
-1.000 0.7745 0.01410 0.00765 -0.2034 0.7678 0.5792
-0.750 0.8048 0.01419 0.00767 -0.2035 0.7623 0.5920
-0.500 0.8278 0.01431 0.00785 -0.2023 0.7536 0.6034
-0.250 0.8577 0.01435 0.00782 -0.2023 0.7472 0.6167
0.000 0.8835 0.01450 0.00796 -0.2018 0.7393 0.6299
0.250 0.9104 0.01451 0.00798 -0.2012 0.7324 0.6390
0.500 0.9389 0.01456 0.00798 -0.2012 0.7248 0.6484
0.750 0.9654 0.01456 0.00798 -0.2007 0.7167 0.6556
1.000 0.9945 0.01460 0.00795 -0.2008 0.7087 0.6650
1.250 1.0203 0.01458 0.00796 -0.2002 0.7000 0.6718
1.500 1.0487 0.01462 0.00795 -0.2002 0.6918 0.6811
1.750 1.0749 0.01462 0.00797 -0.1997 0.6835 0.6882
2.000 1.1031 0.01468 0.00800 -0.1997 0.6755 0.6978
2.250 1.1289 0.01470 0.00804 -0.1991 0.6669 0.7054
2.500 1.1565 0.01479 0.00811 -0.1990 0.6581 0.7151
2.750 1.1820 0.01479 0.00811 -0.1983 0.6482 0.7229
3.000 1.2074 0.01484 0.00817 -0.1978 0.6362 0.7326
3.250 1.2319 0.01484 0.00818 -0.1969 0.6243 0.7403
3.500 1.2591 0.01488 0.00814 -0.1966 0.6126 0.7503
3.750 1.2818 0.01495 0.00826 -0.1955 0.5999 0.7587
4.000 1.3065 0.01508 0.00841 -0.1949 0.5877 0.7692
4.250 1.3308 0.01521 0.00854 -0.1941 0.5760 0.7802
4.500 1.3545 0.01534 0.00868 -0.1932 0.5642 0.7915
4.750 1.3781 0.01550 0.00890 -0.1924 0.5525 0.8044
5.000 1.4017 0.01569 0.00909 -0.1915 0.5416 0.8189
5.250 1.4244 0.01589 0.00929 -0.1905 0.5303 0.8350
5.500 1.4444 0.01607 0.00956 -0.1890 0.5176 0.8529
5.750 1.4626 0.01622 0.00977 -0.1871 0.5052 0.8752
6.000 1.4751 0.01629 0.00988 -0.1839 0.4938 0.9166
6.250 1.4964 0.01652 0.01010 -0.1829 0.4812 1.0000
6.500 1.5214 0.01696 0.01050 -0.1827 0.4665 1.0000
6.750 1.5438 0.01740 0.01092 -0.1821 0.4513 1.0000
7.000 1.5645 0.01786 0.01136 -0.1810 0.4362 1.0000
7.250 1.5829 0.01838 0.01183 -0.1795 0.4206 1.0000
7.500 1.6001 0.01895 0.01235 -0.1778 0.4064 1.0000
7.750 1.6154 0.01952 0.01291 -0.1758 0.3926 1.0000
8.000 1.6292 0.02012 0.01353 -0.1735 0.3775 1.0000
8.250 1.6412 0.02080 0.01419 -0.1710 0.3623 1.0000
8.500 1.6511 0.02162 0.01495 -0.1682 0.3480 1.0000
8.750 1.6605 0.02250 0.01581 -0.1655 0.3323 1.0000
9.000 1.6707 0.02336 0.01673 -0.1630 0.3138 1.0000
9.250 1.6765 0.02449 0.01781 -0.1600 0.2956 1.0000
9.500 1.6813 0.02579 0.01907 -0.1570 0.2789 1.0000
9.750 1.6865 0.02715 0.02043 -0.1543 0.2582 1.0000
10.000 1.6862 0.02895 0.02213 -0.1512 0.2384 1.0000
10.250 1.6856 0.03093 0.02405 -0.1483 0.2207 1.0000
10.500 1.6859 0.03299 0.02608 -0.1458 0.1959 1.0000
10.750 1.6802 0.03567 0.02863 -0.1430 0.1770 1.0000
11.000 1.6763 0.03840 0.03131 -0.1406 0.1551 1.0000
11.250 1.6700 0.04149 0.03429 -0.1384 0.1382 1.0000
11.500 1.6620 0.04490 0.03761 -0.1364 0.1277 1.0000
11.750 1.6618 0.04769 0.04047 -0.1349 0.1179 1.0000
12.000 1.6608 0.05065 0.04345 -0.1336 0.1113 1.0000
12.250 1.6633 0.05332 0.04617 -0.1326 0.1056 1.0000
12.500 1.6624 0.05645 0.04929 -0.1316 0.1015 1.0000
12.750 1.6654 0.05920 0.05214 -0.1309 0.0976 1.0000
13.000 1.6658 0.06233 0.05528 -0.1302 0.0943 1.0000
13.250 1.6632 0.06586 0.05878 -0.1295 0.0909 1.0000
13.500 1.6685 0.06854 0.06160 -0.1291 0.0880 1.0000
13.750 1.6720 0.07147 0.06464 -0.1289 0.0849 1.0000
14.000 1.6742 0.07460 0.06784 -0.1286 0.0825 1.0000
14.250 1.6756 0.07781 0.07104 -0.1283 0.0802 1.0000
14.500 1.6807 0.08064 0.07400 -0.1282 0.0783 1.0000
14.750 1.6858 0.08352 0.07705 -0.1282 0.0763 1.0000
15.000 1.6904 0.08649 0.08015 -0.1284 0.0743 1.0000
15.250 1.6942 0.08959 0.08335 -0.1286 0.0725 1.0000
15.500 1.6968 0.09287 0.08669 -0.1290 0.0707 1.0000
15.750 1.6991 0.09615 0.09001 -0.1293 0.0688 1.0000
16.000 1.7021 0.09949 0.09354 -0.1299 0.0671 1.0000
16.250 1.7036 0.10311 0.09729 -0.1308 0.0649 1.0000
16.500 1.7047 0.10678 0.10106 -0.1318 0.0632 1.0000
16.750 1.7047 0.11058 0.10487 -0.1328 0.0611 1.0000
17.000 1.7075 0.11381 0.10814 -0.1335 0.0592 1.0000
17.250 1.7078 0.11770 0.11223 -0.1348 0.0577 1.0000
17.500 1.7070 0.12182 0.11650 -0.1364 0.0557 1.0000
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