WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il) Reynolds number: 500,000 Max Cl/Cd: 119.12 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63137-il-500000.txt Download as CSV file: xf-fx63137-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4234 0.06143 0.05891 -0.0974 0.9842 0.0123
-11.250 -0.4620 0.04389 0.04101 -0.1184 0.9723 0.0121
-11.000 -0.4661 0.03660 0.03349 -0.1288 0.9595 0.0120
-10.750 -0.4562 0.02923 0.02569 -0.1419 0.9466 0.0123
-10.500 -0.4212 0.02627 0.02257 -0.1503 0.9407 0.0126
-10.250 -0.3842 0.02447 0.02064 -0.1563 0.9342 0.0130
-10.000 -0.3415 0.02259 0.01855 -0.1628 0.9309 0.0137
-9.750 -0.2987 0.02052 0.01604 -0.1691 0.9261 0.0151
-9.500 -0.2591 0.01942 0.01492 -0.1733 0.9197 0.0161
-9.250 -0.2148 0.01840 0.01368 -0.1782 0.9147 0.0176
-9.000 -0.1784 0.01729 0.01238 -0.1814 0.9064 0.0189
-8.750 -0.1400 0.01671 0.01172 -0.1844 0.8989 0.0203
-8.500 -0.1066 0.01615 0.01098 -0.1863 0.8901 0.0213
-8.250 -0.0727 0.01536 0.01005 -0.1884 0.8820 0.0223
-8.000 -0.0428 0.01508 0.00973 -0.1893 0.8733 0.0233
-7.750 -0.0113 0.01476 0.00929 -0.1904 0.8653 0.0243
-7.500 0.0176 0.01436 0.00876 -0.1910 0.8572 0.0250
-7.250 0.0476 0.01388 0.00816 -0.1918 0.8493 0.0255
-7.000 0.0766 0.01354 0.00777 -0.1924 0.8417 0.0262
-6.750 0.1058 0.01342 0.00760 -0.1928 0.8344 0.0272
-6.500 0.1362 0.01326 0.00734 -0.1935 0.8284 0.0283
-6.250 0.1644 0.01301 0.00701 -0.1937 0.8219 0.0291
-6.000 0.1943 0.01264 0.00658 -0.1944 0.8159 0.0299
-5.750 0.2238 0.01247 0.00639 -0.1949 0.8100 0.0310
-5.500 0.2526 0.01220 0.00607 -0.1953 0.8034 0.0318
-5.250 0.2832 0.01191 0.00569 -0.1960 0.7974 0.0324
-5.000 0.3128 0.01163 0.00537 -0.1964 0.7913 0.0330
-4.750 0.3428 0.01138 0.00505 -0.1970 0.7853 0.0336
-4.500 0.3747 0.01108 0.00470 -0.1980 0.7800 0.0347
-4.250 0.4042 0.01086 0.00448 -0.1985 0.7738 0.0364
-4.000 0.4342 0.01067 0.00424 -0.1990 0.7672 0.0381
-3.750 0.4657 0.01046 0.00395 -0.1998 0.7613 0.0396
-3.500 0.4968 0.01013 0.00362 -0.2007 0.7545 0.0423
-3.250 0.5282 0.00991 0.00334 -0.2015 0.7481 0.0484
-3.000 0.5588 0.00972 0.00320 -0.2021 0.7413 0.0637
-2.750 0.5899 0.00949 0.00303 -0.2029 0.7341 0.0913
-2.500 0.6220 0.00923 0.00289 -0.2040 0.7271 0.1564
-2.250 0.6545 0.00887 0.00278 -0.2053 0.7190 0.2516
-2.000 0.6861 0.00869 0.00273 -0.2063 0.7119 0.3255
-1.750 0.7160 0.00858 0.00274 -0.2068 0.7041 0.3771
-1.500 0.7454 0.00856 0.00276 -0.2071 0.6975 0.4144
-1.250 0.7746 0.00856 0.00280 -0.2073 0.6911 0.4429
-1.000 0.8032 0.00859 0.00284 -0.2073 0.6845 0.4622
-0.750 0.8317 0.00866 0.00287 -0.2074 0.6782 0.4792
-0.500 0.8601 0.00871 0.00295 -0.2074 0.6713 0.4983
-0.250 0.8882 0.00881 0.00302 -0.2073 0.6648 0.5163
0.000 0.9163 0.00889 0.00311 -0.2073 0.6581 0.5313
0.250 0.9443 0.00898 0.00317 -0.2072 0.6506 0.5425
0.500 0.9721 0.00906 0.00325 -0.2071 0.6436 0.5518
0.750 0.9998 0.00913 0.00331 -0.2070 0.6350 0.5614
1.000 1.0268 0.00922 0.00338 -0.2067 0.6249 0.5699
1.250 1.0530 0.00936 0.00344 -0.2063 0.6127 0.5787
1.500 1.0792 0.00948 0.00355 -0.2058 0.5994 0.5881
1.750 1.1056 0.00961 0.00366 -0.2055 0.5863 0.5983
2.000 1.1319 0.00975 0.00378 -0.2051 0.5739 0.6084
2.250 1.1579 0.00990 0.00390 -0.2047 0.5616 0.6168
2.500 1.1840 0.01007 0.00404 -0.2043 0.5501 0.6249
2.750 1.2100 0.01024 0.00417 -0.2039 0.5387 0.6318
3.000 1.2354 0.01043 0.00434 -0.2034 0.5268 0.6386
3.250 1.2611 0.01063 0.00451 -0.2030 0.5134 0.6466
3.500 1.2865 0.01080 0.00468 -0.2025 0.4991 0.6537
3.750 1.3110 0.01105 0.00488 -0.2019 0.4848 0.6612
4.000 1.3354 0.01131 0.00510 -0.2013 0.4707 0.6682
4.250 1.3596 0.01157 0.00533 -0.2006 0.4557 0.6760
4.500 1.3836 0.01185 0.00557 -0.2000 0.4383 0.6840
4.750 1.4065 0.01216 0.00584 -0.1991 0.4223 0.6923
5.000 1.4295 0.01249 0.00613 -0.1983 0.4094 0.7013
5.250 1.4520 0.01283 0.00646 -0.1973 0.3965 0.7109
5.500 1.4754 0.01312 0.00675 -0.1966 0.3812 0.7213
5.750 1.4970 0.01349 0.00709 -0.1955 0.3637 0.7337
6.000 1.5169 0.01394 0.00749 -0.1942 0.3483 0.7467
6.250 1.5369 0.01438 0.00791 -0.1928 0.3322 0.7606
6.500 1.5570 0.01478 0.00831 -0.1915 0.3105 0.7757
6.750 1.5717 0.01539 0.00883 -0.1893 0.2890 0.7927
7.000 1.5875 0.01589 0.00933 -0.1872 0.2729 0.8136
7.250 1.6009 0.01646 0.00989 -0.1847 0.2498 0.8411
7.500 1.6066 0.01700 0.01045 -0.1807 0.2330 0.9042
7.750 1.6153 0.01758 0.01100 -0.1774 0.2211 1.0000
8.000 1.6295 0.01832 0.01169 -0.1753 0.2009 1.0000
8.500 1.6485 0.02037 0.01353 -0.1700 0.1670 1.0000
9.000 1.6622 0.02290 0.01583 -0.1645 0.1267 1.0000
9.250 1.6712 0.02408 0.01699 -0.1621 0.1083 1.0000
9.500 1.6754 0.02566 0.01845 -0.1594 0.0947 1.0000
9.750 1.6840 0.02699 0.01978 -0.1573 0.0876 1.0000
10.000 1.6913 0.02846 0.02126 -0.1552 0.0818 1.0000
10.250 1.7017 0.02974 0.02259 -0.1535 0.0771 1.0000
10.500 1.7118 0.03108 0.02396 -0.1519 0.0711 1.0000
10.750 1.7191 0.03270 0.02557 -0.1501 0.0672 1.0000
11.000 1.7269 0.03434 0.02723 -0.1485 0.0648 1.0000
11.250 1.7335 0.03614 0.02905 -0.1470 0.0624 1.0000
11.500 1.7391 0.03809 0.03103 -0.1454 0.0602 1.0000
11.750 1.7464 0.03992 0.03295 -0.1441 0.0588 1.0000
12.000 1.7530 0.04188 0.03500 -0.1429 0.0574 1.0000
12.250 1.7573 0.04414 0.03732 -0.1416 0.0556 1.0000
12.500 1.7602 0.04661 0.03985 -0.1404 0.0540 1.0000
12.750 1.7619 0.04930 0.04261 -0.1393 0.0525 1.0000
13.000 1.7613 0.05236 0.04575 -0.1382 0.0510 1.0000
13.250 1.7684 0.05455 0.04804 -0.1376 0.0499 1.0000
13.500 1.7775 0.05655 0.05013 -0.1371 0.0488 1.0000
13.750 1.7862 0.05862 0.05228 -0.1366 0.0466 1.0000
14.000 1.7907 0.06128 0.05500 -0.1361 0.0446 1.0000
14.250 1.7917 0.06446 0.05825 -0.1357 0.0430 1.0000
14.500 1.7975 0.06707 0.06092 -0.1355 0.0411 1.0000
14.750 1.8097 0.06880 0.06271 -0.1353 0.0382 1.0000
15.000 1.8142 0.07163 0.06558 -0.1352 0.0352 1.0000
15.250 1.8189 0.07450 0.06847 -0.1351 0.0299 1.0000
15.500 1.8116 0.07917 0.07303 -0.1354 0.0203 1.0000
15.750 1.7945 0.08550 0.07936 -0.1360 0.0102 1.0000
16.000 1.7802 0.09160 0.08553 -0.1368 0.0069 1.0000
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