FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 200,000 Max Cl/Cd: 88.87 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137sm-il-200000-n5.txt Download as CSV file: xf-fx63137sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-137 13.7% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1616 0.11682 0.11309 -0.0676 0.9777 0.0308
-10.500 -0.1506 0.11288 0.10916 -0.0708 0.9725 0.0313
-10.250 -0.1531 0.10483 0.10110 -0.0762 0.9654 0.0238
-10.000 -0.1380 0.10248 0.09875 -0.0772 0.9583 0.0226
-9.500 -0.1207 0.09377 0.09005 -0.0833 0.9434 0.0213
-9.250 -0.1146 0.08750 0.08377 -0.0885 0.9377 0.0204
-9.000 -0.1048 0.08340 0.07967 -0.0919 0.9294 0.0207
-8.750 -0.0935 0.07797 0.07424 -0.0975 0.9238 0.0207
-8.250 -0.1454 0.03782 0.03326 -0.1486 0.8915 0.0197
-8.000 -0.1219 0.03140 0.02614 -0.1605 0.8804 0.0198
-7.750 -0.0851 0.02832 0.02271 -0.1668 0.8751 0.0201
-7.500 -0.0548 0.02623 0.02036 -0.1702 0.8674 0.0206
-7.250 -0.0197 0.02429 0.01810 -0.1738 0.8611 0.0211
-7.000 0.0160 0.02249 0.01598 -0.1771 0.8554 0.0217
-6.750 0.0466 0.02108 0.01428 -0.1788 0.8478 0.0225
-6.500 0.0819 0.01983 0.01267 -0.1811 0.8419 0.0237
-6.250 0.1117 0.01904 0.01185 -0.1821 0.8351 0.0247
-6.000 0.1425 0.01824 0.01094 -0.1832 0.8283 0.0257
-5.500 0.2043 0.01676 0.00919 -0.1851 0.8155 0.0277
-5.250 0.2363 0.01610 0.00849 -0.1864 0.8092 0.0289
-5.000 0.2686 0.01561 0.00794 -0.1876 0.8033 0.0308
-4.750 0.2990 0.01516 0.00743 -0.1885 0.7964 0.0334
-4.500 0.3323 0.01472 0.00694 -0.1899 0.7905 0.0362
-4.250 0.3647 0.01430 0.00645 -0.1911 0.7843 0.0396
-4.000 0.3964 0.01397 0.00607 -0.1922 0.7776 0.0454
-3.750 0.4306 0.01361 0.00568 -0.1937 0.7720 0.0558
-3.500 0.4625 0.01326 0.00540 -0.1949 0.7654 0.0779
-3.250 0.4960 0.01287 0.00513 -0.1965 0.7589 0.1248
-3.000 0.5328 0.01233 0.00488 -0.1990 0.7536 0.2271
-2.750 0.5653 0.01202 0.00492 -0.2004 0.7465 0.3398
-2.500 0.5961 0.01199 0.00495 -0.2010 0.7402 0.3977
-2.250 0.6258 0.01203 0.00498 -0.2013 0.7341 0.4310
-2.000 0.6545 0.01209 0.00500 -0.2013 0.7271 0.4518
-1.750 0.6841 0.01215 0.00498 -0.2015 0.7211 0.4689
-1.500 0.7123 0.01222 0.00505 -0.2014 0.7141 0.4891
-1.250 0.7408 0.01231 0.00510 -0.2014 0.7074 0.5075
-1.000 0.7694 0.01237 0.00512 -0.2014 0.7011 0.5176
-0.750 0.7976 0.01244 0.00514 -0.2014 0.6938 0.5277
-0.500 0.8261 0.01250 0.00516 -0.2014 0.6874 0.5356
-0.250 0.8542 0.01258 0.00519 -0.2014 0.6802 0.5451
0.000 0.8820 0.01264 0.00525 -0.2013 0.6730 0.5526
0.250 0.9102 0.01273 0.00529 -0.2013 0.6662 0.5619
0.500 0.9374 0.01281 0.00538 -0.2010 0.6584 0.5695
0.750 0.9656 0.01292 0.00542 -0.2010 0.6518 0.5786
1.000 0.9924 0.01301 0.00554 -0.2007 0.6435 0.5866
1.250 1.0203 0.01313 0.00561 -0.2007 0.6364 0.5958
1.500 1.0469 0.01323 0.00575 -0.2004 0.6281 0.6040
1.750 1.0743 0.01336 0.00584 -0.2002 0.6203 0.6136
2.000 1.1007 0.01348 0.00600 -0.1999 0.6118 0.6221
2.250 1.1277 0.01363 0.00611 -0.1996 0.6036 0.6318
2.500 1.1538 0.01376 0.00630 -0.1992 0.5949 0.6408
3.000 1.2059 0.01408 0.00663 -0.1985 0.5771 0.6604
3.250 1.2320 0.01427 0.00679 -0.1981 0.5684 0.6708
3.500 1.2572 0.01444 0.00702 -0.1976 0.5586 0.6814
3.750 1.2825 0.01464 0.00723 -0.1970 0.5494 0.6918
4.000 1.3076 0.01485 0.00746 -0.1965 0.5395 0.7033
4.250 1.3321 0.01506 0.00772 -0.1958 0.5297 0.7145
4.500 1.3562 0.01530 0.00796 -0.1951 0.5198 0.7262
4.750 1.3802 0.01553 0.00824 -0.1944 0.5092 0.7387
5.000 1.4030 0.01580 0.00853 -0.1934 0.4972 0.7517
5.250 1.4240 0.01610 0.00882 -0.1921 0.4820 0.7650
5.500 1.4435 0.01645 0.00914 -0.1906 0.4640 0.7790
5.750 1.4616 0.01683 0.00948 -0.1887 0.4442 0.7943
6.000 1.4790 0.01724 0.00987 -0.1868 0.4261 0.8110
6.250 1.4963 0.01764 0.01026 -0.1849 0.4107 0.8297
6.500 1.5125 0.01803 0.01067 -0.1828 0.3967 0.8522
6.750 1.5252 0.01840 0.01106 -0.1800 0.3832 0.8837
7.000 1.5321 0.01872 0.01141 -0.1760 0.3701 1.0000
7.500 1.5627 0.02000 0.01260 -0.1722 0.3394 1.0000
7.750 1.5769 0.02071 0.01328 -0.1701 0.3244 1.0000
8.000 1.5899 0.02149 0.01403 -0.1680 0.3092 1.0000
8.250 1.6013 0.02237 0.01487 -0.1656 0.2933 1.0000
8.500 1.6114 0.02335 0.01581 -0.1632 0.2770 1.0000
8.750 1.6204 0.02443 0.01686 -0.1607 0.2605 1.0000
9.000 1.6284 0.02563 0.01801 -0.1583 0.2442 1.0000
9.250 1.6357 0.02692 0.01927 -0.1559 0.2283 1.0000
9.500 1.6421 0.02835 0.02066 -0.1535 0.2124 1.0000
9.750 1.6476 0.02992 0.02219 -0.1512 0.1962 1.0000
10.000 1.6521 0.03164 0.02388 -0.1490 0.1800 1.0000
10.250 1.6557 0.03352 0.02572 -0.1468 0.1645 1.0000
10.500 1.6586 0.03553 0.02770 -0.1448 0.1506 1.0000
10.750 1.6611 0.03768 0.02983 -0.1429 0.1390 1.0000
11.000 1.6653 0.03976 0.03192 -0.1413 0.1294 1.0000
11.250 1.6685 0.04199 0.03419 -0.1398 0.1221 1.0000
11.500 1.6721 0.04426 0.03650 -0.1384 0.1160 1.0000
11.750 1.6744 0.04674 0.03902 -0.1371 0.1111 1.0000
12.000 1.6791 0.04904 0.04140 -0.1360 0.1066 1.0000
12.250 1.6814 0.05165 0.04407 -0.1349 0.1027 1.0000
12.500 1.6814 0.05461 0.04706 -0.1339 0.0995 1.0000
12.750 1.6868 0.05702 0.04961 -0.1332 0.0965 1.0000
13.000 1.6903 0.05971 0.05239 -0.1325 0.0938 1.0000
13.250 1.6924 0.06263 0.05539 -0.1319 0.0914 1.0000
13.500 1.6931 0.06579 0.05862 -0.1314 0.0893 1.0000
13.750 1.6924 0.06920 0.06207 -0.1310 0.0874 1.0000
14.000 1.6972 0.07194 0.06496 -0.1307 0.0857 1.0000
14.250 1.7011 0.07485 0.06799 -0.1305 0.0838 1.0000
14.500 1.7045 0.07786 0.07112 -0.1304 0.0820 1.0000
14.750 1.7066 0.08109 0.07445 -0.1304 0.0802 1.0000
15.000 1.7081 0.08445 0.07788 -0.1305 0.0787 1.0000
15.250 1.7090 0.08788 0.08137 -0.1306 0.0773 1.0000
15.500 1.7108 0.09118 0.08472 -0.1307 0.0760 1.0000
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Polar data table (+)
Polar graphs
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