FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 200,000 Max Cl/Cd: 91.53 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137sm-il-200000.txt Download as CSV file: xf-fx63137sm-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0995 0.09232 0.08889 -0.0845 0.9554 0.0562
-8.250 -0.0813 0.08813 0.08469 -0.0901 0.9520 0.0591
-8.000 -0.0934 0.08050 0.07712 -0.1036 0.9397 0.0620
-7.750 -0.0602 0.07875 0.07534 -0.1010 0.9391 0.0636
-7.500 -0.0331 0.07592 0.07250 -0.1041 0.9373 0.0674
-7.250 -0.0562 0.06513 0.06168 -0.1264 0.9167 0.0719
-7.000 -0.0146 0.06575 0.06234 -0.1172 0.9226 0.0746
-6.750 -0.0016 0.06362 0.06021 -0.1176 0.9132 0.0767
-6.500 0.0116 0.04860 0.04487 -0.1510 0.8999 0.0857
-6.250 0.0422 0.04696 0.04333 -0.1503 0.8968 0.0880
-6.000 0.1096 0.02588 0.01987 -0.1803 0.8922 0.0441
-5.750 0.1451 0.02361 0.01721 -0.1829 0.8862 0.0443
-5.500 0.1836 0.02169 0.01491 -0.1857 0.8808 0.0456
-5.250 0.2247 0.01991 0.01297 -0.1887 0.8771 0.0466
-5.000 0.2643 0.01866 0.01162 -0.1910 0.8730 0.0481
-4.750 0.2907 0.01793 0.01081 -0.1908 0.8648 0.0500
-4.500 0.3288 0.01701 0.00979 -0.1927 0.8600 0.0534
-4.250 0.3625 0.01631 0.00914 -0.1941 0.8541 0.0586
-4.000 0.3943 0.01561 0.00845 -0.1951 0.8468 0.0642
-3.750 0.4348 0.01490 0.00775 -0.1979 0.8418 0.0774
-3.500 0.4726 0.01407 0.00710 -0.2006 0.8350 0.1229
-3.250 0.5172 0.01294 0.00686 -0.2054 0.8288 0.3733
-3.000 0.5523 0.01300 0.00688 -0.2065 0.8234 0.4332
-2.750 0.5777 0.01321 0.00710 -0.2058 0.8153 0.4653
-2.500 0.6082 0.01338 0.00720 -0.2060 0.8089 0.4942
-2.250 0.6367 0.01356 0.00735 -0.2057 0.8025 0.5148
-2.000 0.6637 0.01369 0.00744 -0.2053 0.7949 0.5308
-1.750 0.6957 0.01377 0.00740 -0.2058 0.7892 0.5464
-1.500 0.7201 0.01396 0.00761 -0.2048 0.7814 0.5618
-1.250 0.7480 0.01406 0.00770 -0.2044 0.7747 0.5767
-1.000 0.7765 0.01413 0.00773 -0.2043 0.7684 0.5873
-0.750 0.8047 0.01420 0.00773 -0.2043 0.7606 0.5986
-0.500 0.8346 0.01420 0.00769 -0.2044 0.7549 0.6068
-0.250 0.8612 0.01429 0.00776 -0.2041 0.7467 0.6171
0.000 0.8896 0.01430 0.00775 -0.2040 0.7401 0.6254
0.250 0.9183 0.01437 0.00778 -0.2041 0.7330 0.6355
0.500 0.9449 0.01442 0.00783 -0.2036 0.7254 0.6442
0.750 0.9758 0.01445 0.00779 -0.2041 0.7192 0.6542
1.000 1.0004 0.01454 0.00793 -0.2033 0.7106 0.6635
1.250 1.0305 0.01456 0.00788 -0.2036 0.7041 0.6733
1.500 1.0560 0.01468 0.00803 -0.2031 0.6955 0.6839
1.750 1.0841 0.01470 0.00804 -0.2029 0.6883 0.6931
2.000 1.1105 0.01481 0.00817 -0.2025 0.6800 0.7044
2.250 1.1376 0.01486 0.00821 -0.2022 0.6722 0.7146
2.500 1.1635 0.01496 0.00834 -0.2017 0.6639 0.7252
2.750 1.1912 0.01503 0.00839 -0.2016 0.6556 0.7375
3.000 1.2160 0.01514 0.00854 -0.2008 0.6471 0.7485
3.250 1.2423 0.01521 0.00861 -0.2004 0.6386 0.7601
3.500 1.2676 0.01533 0.00879 -0.1998 0.6295 0.7730
3.750 1.2943 0.01543 0.00886 -0.1994 0.6210 0.7869
4.000 1.3172 0.01555 0.00906 -0.1983 0.6113 0.7998
4.250 1.3433 0.01564 0.00913 -0.1978 0.6029 0.8140
4.500 1.3651 0.01577 0.00936 -0.1966 0.5925 0.8295
4.750 1.3897 0.01588 0.00946 -0.1958 0.5836 0.8463
5.000 1.4107 0.01596 0.00960 -0.1943 0.5721 0.8654
5.250 1.4285 0.01600 0.00969 -0.1922 0.5596 0.8873
5.500 1.4433 0.01596 0.00967 -0.1893 0.5468 0.9200
5.750 1.4627 0.01598 0.00967 -0.1877 0.5324 1.0000
6.000 1.4899 0.01628 0.00991 -0.1879 0.5176 1.0000
6.250 1.5154 0.01662 0.01021 -0.1877 0.5038 1.0000
6.500 1.5391 0.01697 0.01057 -0.1872 0.4900 1.0000
6.750 1.5617 0.01736 0.01095 -0.1864 0.4762 1.0000
7.000 1.5829 0.01777 0.01133 -0.1854 0.4621 1.0000
7.250 1.6030 0.01822 0.01175 -0.1841 0.4479 1.0000
7.500 1.6218 0.01871 0.01221 -0.1826 0.4338 1.0000
7.750 1.6389 0.01924 0.01271 -0.1808 0.4191 1.0000
8.000 1.6536 0.01981 0.01326 -0.1787 0.4039 1.0000
8.250 1.6657 0.02041 0.01386 -0.1760 0.3884 1.0000
8.500 1.6767 0.02110 0.01453 -0.1733 0.3728 1.0000
8.750 1.6865 0.02186 0.01529 -0.1704 0.3569 1.0000
9.000 1.6951 0.02273 0.01614 -0.1675 0.3408 1.0000
9.250 1.7022 0.02372 0.01711 -0.1645 0.3240 1.0000
9.500 1.7072 0.02488 0.01823 -0.1613 0.3065 1.0000
9.750 1.7113 0.02617 0.01950 -0.1582 0.2873 1.0000
10.000 1.7133 0.02769 0.02098 -0.1551 0.2667 1.0000
10.250 1.7118 0.02956 0.02277 -0.1518 0.2453 1.0000
10.500 1.7092 0.03168 0.02481 -0.1488 0.2228 1.0000
10.750 1.7044 0.03414 0.02717 -0.1458 0.2009 1.0000
11.000 1.6985 0.03689 0.02983 -0.1431 0.1826 1.0000
11.250 1.6939 0.03972 0.03257 -0.1407 0.1677 1.0000
11.500 1.6926 0.04238 0.03521 -0.1388 0.1559 1.0000
11.750 1.6924 0.04504 0.03789 -0.1371 0.1469 1.0000
12.000 1.6901 0.04799 0.04078 -0.1355 0.1401 1.0000
12.250 1.6940 0.05042 0.04329 -0.1343 0.1340 1.0000
12.500 1.6960 0.05308 0.04597 -0.1331 0.1290 1.0000
12.750 1.6981 0.05582 0.04868 -0.1319 0.1248 1.0000
13.000 1.7048 0.05810 0.05109 -0.1310 0.1210 1.0000
13.250 1.7105 0.06050 0.05356 -0.1302 0.1175 1.0000
13.500 1.7161 0.06296 0.05600 -0.1294 0.1143 1.0000
13.750 1.7249 0.06509 0.05814 -0.1285 0.1111 1.0000
14.000 1.7323 0.06741 0.06062 -0.1279 0.1085 1.0000
14.250 1.7400 0.06969 0.06300 -0.1273 0.1059 1.0000
14.500 1.7487 0.07187 0.06524 -0.1267 0.1036 1.0000
14.750 1.7606 0.07368 0.06703 -0.1260 0.1012 1.0000
15.000 1.7758 0.07522 0.06860 -0.1251 0.0987 1.0000
15.250 1.7804 0.07794 0.07153 -0.1248 0.0970 1.0000
15.500 1.7864 0.08051 0.07426 -0.1245 0.0952 1.0000
15.750 1.7944 0.08285 0.07673 -0.1241 0.0933 1.0000
16.000 1.8027 0.08513 0.07909 -0.1238 0.0915 1.0000
16.250 1.8145 0.08697 0.08095 -0.1234 0.0896 1.0000
16.500 1.8352 0.08806 0.08207 -0.1226 0.0871 1.0000
16.750 1.8337 0.09152 0.08576 -0.1227 0.0861 1.0000
17.000 1.8326 0.09501 0.08947 -0.1229 0.0848 1.0000
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Polar data table (+)
Polar graphs
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