WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il) Reynolds number: 100,000 Max Cl/Cd: 63.92 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137-il-100000-n5.txt Download as CSV file: xf-fx63137-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1622 0.09581 0.09092 -0.0773 0.9536 0.0318
-9.000 -0.1556 0.09046 0.08557 -0.0819 0.9471 0.0324
-8.750 -0.1583 0.08346 0.07860 -0.0877 0.9387 0.0335
-8.500 -0.1464 0.07986 0.07501 -0.0913 0.9323 0.0350
-8.250 -0.1431 0.07473 0.06989 -0.0962 0.9245 0.0380
-8.000 -0.1597 0.06382 0.05897 -0.1064 0.9140 0.0386
-7.750 -0.1747 0.05317 0.04814 -0.1205 0.8994 0.0382
-7.500 -0.1657 0.04578 0.04032 -0.1341 0.8881 0.0401
-7.250 -0.1348 0.04192 0.03608 -0.1420 0.8830 0.0433
-7.000 -0.0904 0.03535 0.02842 -0.1544 0.8800 0.0451
-6.750 -0.0685 0.03331 0.02615 -0.1556 0.8716 0.0456
-6.500 -0.0320 0.03108 0.02360 -0.1591 0.8679 0.0462
-6.250 0.0067 0.02927 0.02153 -0.1626 0.8651 0.0472
-6.000 0.0438 0.02774 0.01971 -0.1654 0.8618 0.0488
-5.750 0.0712 0.02655 0.01828 -0.1661 0.8550 0.0499
-5.500 0.1072 0.02521 0.01668 -0.1681 0.8510 0.0507
-5.250 0.1454 0.02400 0.01524 -0.1703 0.8479 0.0516
-5.000 0.1740 0.02322 0.01445 -0.1707 0.8419 0.0527
-4.750 0.2050 0.02250 0.01371 -0.1715 0.8361 0.0542
-4.500 0.2421 0.02171 0.01285 -0.1733 0.8320 0.0564
-4.250 0.2751 0.02112 0.01215 -0.1744 0.8265 0.0592
-4.000 0.3057 0.02059 0.01166 -0.1753 0.8198 0.0630
-3.750 0.3440 0.01998 0.01096 -0.1777 0.8156 0.0703
-3.500 0.3838 0.01938 0.01036 -0.1805 0.8120 0.0826
-3.250 0.4137 0.01905 0.01008 -0.1815 0.8052 0.1041
-3.000 0.4555 0.01820 0.00954 -0.1852 0.8003 0.1714
-2.750 0.5000 0.01740 0.00934 -0.1892 0.7962 0.3462
-2.500 0.5260 0.01751 0.00957 -0.1889 0.7878 0.4166
-2.250 0.5585 0.01759 0.00963 -0.1894 0.7820 0.4638
-2.000 0.5879 0.01776 0.00975 -0.1894 0.7760 0.4943
-1.750 0.6140 0.01801 0.00996 -0.1888 0.7692 0.5196
-1.500 0.6452 0.01815 0.01003 -0.1890 0.7641 0.5446
-1.250 0.6700 0.01838 0.01024 -0.1882 0.7571 0.5625
-1.000 0.6983 0.01848 0.01026 -0.1880 0.7505 0.5763
-0.750 0.7285 0.01846 0.01018 -0.1881 0.7447 0.5853
-0.500 0.7547 0.01858 0.01024 -0.1878 0.7362 0.5961
-0.250 0.7854 0.01855 0.01015 -0.1880 0.7303 0.6053
0.000 0.8111 0.01870 0.01027 -0.1876 0.7225 0.6147
0.250 0.8396 0.01875 0.01028 -0.1876 0.7160 0.6225
0.500 0.8692 0.01882 0.01029 -0.1879 0.7097 0.6314
0.750 0.8939 0.01895 0.01045 -0.1873 0.7018 0.6388
1.000 0.9262 0.01895 0.01037 -0.1880 0.6961 0.6484
1.250 0.9484 0.01914 0.01062 -0.1869 0.6872 0.6563
1.500 0.9796 0.01915 0.01057 -0.1874 0.6808 0.6660
1.750 1.0035 0.01932 0.01078 -0.1866 0.6723 0.6739
2.000 1.0337 0.01934 0.01076 -0.1869 0.6648 0.6831
2.250 1.0575 0.01949 0.01095 -0.1861 0.6554 0.6908
2.500 1.0870 0.01952 0.01094 -0.1863 0.6472 0.6998
2.750 1.1093 0.01972 0.01121 -0.1852 0.6371 0.7077
3.000 1.1383 0.01976 0.01121 -0.1852 0.6293 0.7176
3.250 1.1607 0.01997 0.01150 -0.1842 0.6195 0.7269
3.500 1.1883 0.02004 0.01157 -0.1840 0.6114 0.7374
3.750 1.2120 0.02025 0.01183 -0.1832 0.6012 0.7487
4.000 1.2361 0.02038 0.01200 -0.1824 0.5914 0.7598
4.250 1.2603 0.02051 0.01215 -0.1816 0.5804 0.7722
4.500 1.2815 0.02073 0.01243 -0.1803 0.5676 0.7854
4.750 1.3035 0.02089 0.01262 -0.1791 0.5550 0.7997
5.000 1.3255 0.02102 0.01276 -0.1779 0.5428 0.8156
5.250 1.3462 0.02119 0.01296 -0.1764 0.5310 0.8343
5.500 1.3620 0.02142 0.01329 -0.1742 0.5183 0.8586
5.750 1.3737 0.02153 0.01349 -0.1710 0.5059 0.9051
6.000 1.3934 0.02180 0.01376 -0.1696 0.4917 1.0000
6.250 1.4167 0.02224 0.01412 -0.1691 0.4772 1.0000
6.500 1.4377 0.02274 0.01456 -0.1681 0.4620 1.0000
6.750 1.4556 0.02332 0.01515 -0.1667 0.4457 1.0000
7.250 1.4875 0.02454 0.01630 -0.1631 0.4154 1.0000
7.500 1.5022 0.02525 0.01700 -0.1612 0.4011 1.0000
7.750 1.5160 0.02600 0.01780 -0.1592 0.3869 1.0000
8.000 1.5294 0.02680 0.01864 -0.1573 0.3733 1.0000
8.250 1.5411 0.02770 0.01953 -0.1551 0.3591 1.0000
8.500 1.5514 0.02870 0.02050 -0.1528 0.3452 1.0000
8.750 1.5606 0.02980 0.02163 -0.1506 0.3304 1.0000
9.000 1.5696 0.03097 0.02286 -0.1484 0.3141 1.0000
9.250 1.5760 0.03233 0.02421 -0.1461 0.2981 1.0000
9.500 1.5805 0.03390 0.02573 -0.1437 0.2835 1.0000
9.750 1.5859 0.03551 0.02738 -0.1416 0.2675 1.0000
10.000 1.5902 0.03728 0.02918 -0.1395 0.2488 1.0000
10.250 1.5907 0.03941 0.03126 -0.1374 0.2335 1.0000
10.500 1.5921 0.04161 0.03345 -0.1355 0.2199 1.0000
10.750 1.5953 0.04377 0.03567 -0.1339 0.2039 1.0000
11.000 1.5952 0.04631 0.03822 -0.1323 0.1888 1.0000
11.250 1.5932 0.04913 0.04102 -0.1307 0.1771 1.0000
11.500 1.5912 0.05208 0.04397 -0.1294 0.1658 1.0000
11.750 1.5929 0.05477 0.04678 -0.1284 0.1511 1.0000
12.000 1.5895 0.05810 0.05011 -0.1274 0.1402 1.0000
12.250 1.5859 0.06158 0.05361 -0.1266 0.1320 1.0000
12.500 1.5815 0.06527 0.05732 -0.1259 0.1254 1.0000
12.750 1.5816 0.06855 0.06073 -0.1255 0.1176 1.0000
13.000 1.5799 0.07213 0.06438 -0.1251 0.1118 1.0000
13.250 1.5802 0.07554 0.06791 -0.1249 0.1063 1.0000
13.500 1.5778 0.07937 0.07179 -0.1249 0.1023 1.0000
13.750 1.5785 0.08282 0.07534 -0.1249 0.0989 1.0000
14.000 1.5788 0.08639 0.07900 -0.1251 0.0959 1.0000
14.250 1.5787 0.09002 0.08268 -0.1253 0.0933 1.0000
14.500 1.5796 0.09346 0.08611 -0.1255 0.0911 1.0000
14.750 1.5852 0.09626 0.08903 -0.1255 0.0891 1.0000
15.000 1.5908 0.09908 0.09201 -0.1257 0.0870 1.0000
15.250 1.5954 0.10210 0.09514 -0.1260 0.0847 1.0000
15.500 1.5994 0.10516 0.09830 -0.1264 0.0825 1.0000
15.750 1.6034 0.10813 0.10127 -0.1269 0.0801 1.0000
16.000 1.6062 0.11152 0.10484 -0.1277 0.0778 1.0000
16.250 1.6069 0.11533 0.10888 -0.1288 0.0753 1.0000
16.500 1.6075 0.11914 0.11283 -0.1301 0.0729 1.0000
16.750 1.6063 0.12326 0.11705 -0.1318 0.0705 1.0000
17.000 1.6071 0.12699 0.12087 -0.1333 0.0686 1.0000
17.250 1.6067 0.13109 0.12518 -0.1350 0.0667 1.0000
17.500 1.6061 0.13522 0.12948 -0.1370 0.0648 1.0000
17.750 1.6053 0.13938 0.13376 -0.1390 0.0630 1.0000
18.000 1.6048 0.14345 0.13791 -0.1412 0.0614 1.0000
18.250 1.6071 0.14680 0.14122 -0.1429 0.0596 1.0000
18.500 1.6055 0.15124 0.14591 -0.1454 0.0585 1.0000
18.750 1.6032 0.15583 0.15070 -0.1480 0.0571 1.0000
19.000 1.5994 0.16079 0.15584 -0.1511 0.0555 1.0000
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