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WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
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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