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WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il)
Reynolds number: 100,000
Max Cl/Cd: 62.09 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137-il-100000.txt
Download as CSV file: xf-fx63137-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2422   0.10601   0.10184  -0.0571   0.9619   0.1126
  -7.500  -0.2151   0.10132   0.09713  -0.0582   0.9592   0.1177
  -7.250  -0.2169   0.09922   0.09506  -0.0597   0.9504   0.1245
  -7.000  -0.1999   0.09557   0.09141  -0.0621   0.9459   0.1326
  -6.750  -0.2156   0.09427   0.09017  -0.0629   0.9355   0.1392
  -6.500  -0.1983   0.09123   0.08712  -0.0645   0.9308   0.1528
  -6.000  -0.2137   0.08432   0.08029  -0.0802   0.9077   0.1708
  -5.750  -0.1802   0.08369   0.07962  -0.0671   0.9067   0.1806
  -5.500  -0.1712   0.07792   0.07382  -0.0861   0.8972   0.2017
  -5.250  -0.1757   0.07657   0.07253  -0.0789   0.8890   0.2032
  -5.000  -0.0587   0.04293   0.03660  -0.1398   0.8877   0.0991
  -4.750  -0.0091   0.03927   0.03252  -0.1460   0.8847   0.0955
  -4.500   0.0460   0.03648   0.02915  -0.1525   0.8824   0.0946
  -4.250   0.1005   0.03422   0.02640  -0.1579   0.8804   0.0935
  -4.000   0.1218   0.03356   0.02552  -0.1576   0.8722   0.0935
  -3.750   0.1649   0.03227   0.02401  -0.1603   0.8677   0.0949
  -3.500   0.2143   0.03094   0.02249  -0.1637   0.8646   0.0981
  -3.250   0.2388   0.03051   0.02201  -0.1633   0.8562   0.1014
  -3.000   0.2789   0.02951   0.02116  -0.1653   0.8513   0.1102
  -2.750   0.3310   0.02824   0.02009  -0.1696   0.8485   0.1347
  -2.500   0.4042   0.02612   0.01941  -0.1791   0.8475   0.4397
  -2.250   0.4152   0.02723   0.02053  -0.1761   0.8370   0.4923
  -2.000   0.4484   0.02763   0.02091  -0.1757   0.8326   0.5365
  -1.750   0.4874   0.02774   0.02099  -0.1759   0.8302   0.5713
  -1.500   0.4896   0.02884   0.02211  -0.1716   0.8179   0.5883
  -1.250   0.5302   0.02859   0.02181  -0.1720   0.8148   0.6160
  -1.000   0.5397   0.02932   0.02256  -0.1685   0.8038   0.6335
  -0.750   0.5722   0.02910   0.02233  -0.1674   0.7995   0.6575
  -0.500   0.6183   0.02856   0.02169  -0.1693   0.7972   0.6808
  -0.250   0.6210   0.02938   0.02255  -0.1652   0.7850   0.6905
   0.000   0.6672   0.02874   0.02181  -0.1676   0.7820   0.7049
   0.250   0.7158   0.02806   0.02103  -0.1705   0.7798   0.7185
   0.500   0.7199   0.02905   0.02206  -0.1671   0.7673   0.7286
   0.750   0.7642   0.02835   0.02130  -0.1691   0.7644   0.7418
   1.000   0.7798   0.02906   0.02201  -0.1678   0.7533   0.7520
   1.250   0.8227   0.02837   0.02127  -0.1696   0.7493   0.7634
   1.500   0.8690   0.02751   0.02035  -0.1718   0.7464   0.7750
   1.750   0.8826   0.02823   0.02110  -0.1701   0.7343   0.7858
   2.000   0.9291   0.02730   0.02011  -0.1722   0.7307   0.7993
   2.250   0.9407   0.02785   0.02073  -0.1697   0.7191   0.8102
   2.500   0.9850   0.02693   0.01977  -0.1715   0.7146   0.8232
   2.750   1.0034   0.02734   0.02021  -0.1702   0.7038   0.8357
   3.250   1.0594   0.02706   0.01998  -0.1697   0.6888   0.8631
   3.500   1.0933   0.02648   0.01940  -0.1700   0.6826   0.8793
   3.750   1.1115   0.02662   0.01960  -0.1683   0.6734   0.8982
   4.000   1.1373   0.02597   0.01898  -0.1671   0.6662   0.9236
   4.250   1.1593   0.02585   0.01893  -0.1660   0.6560   1.0000
   4.500   1.2160   0.02499   0.01798  -0.1708   0.6479   1.0000
   4.750   1.2503   0.02520   0.01822  -0.1725   0.6357   1.0000
   5.000   1.2948   0.02485   0.01782  -0.1755   0.6258   1.0000
   5.250   1.3362   0.02457   0.01750  -0.1778   0.6153   1.0000
   5.500   1.3658   0.02479   0.01774  -0.1784   0.6030   1.0000
   5.750   1.4006   0.02464   0.01754  -0.1794   0.5911   1.0000
   6.000   1.4384   0.02428   0.01707  -0.1807   0.5791   1.0000
   6.250   1.4621   0.02445   0.01726  -0.1800   0.5649   1.0000
   6.500   1.4863   0.02461   0.01745  -0.1793   0.5510   1.0000
   6.750   1.5109   0.02479   0.01762  -0.1786   0.5370   1.0000
   7.000   1.5352   0.02500   0.01782  -0.1778   0.5230   1.0000
   7.250   1.5590   0.02526   0.01807  -0.1770   0.5092   1.0000
   7.500   1.5840   0.02551   0.01829  -0.1764   0.4961   1.0000
   7.750   1.6024   0.02596   0.01879  -0.1748   0.4819   1.0000
   8.000   1.6198   0.02646   0.01933  -0.1730   0.4670   1.0000
   8.250   1.6351   0.02702   0.01994  -0.1709   0.4516   1.0000
   8.500   1.6490   0.02761   0.02057  -0.1687   0.4364   1.0000
   8.750   1.6619   0.02821   0.02118  -0.1662   0.4209   1.0000
   9.000   1.6718   0.02890   0.02189  -0.1633   0.4054   1.0000
   9.250   1.6780   0.02974   0.02276  -0.1600   0.3894   1.0000
   9.500   1.6810   0.03072   0.02378  -0.1563   0.3728   1.0000
   9.750   1.6839   0.03180   0.02487  -0.1528   0.3563   1.0000
  10.000   1.6858   0.03307   0.02614  -0.1494   0.3394   1.0000
  10.250   1.6849   0.03460   0.02772  -0.1460   0.3213   1.0000
  10.500   1.6822   0.03634   0.02945  -0.1426   0.3029   1.0000
  10.750   1.6786   0.03835   0.03135  -0.1394   0.2845   1.0000
  11.000   1.6714   0.04084   0.03390  -0.1363   0.2628   1.0000
  11.250   1.6626   0.04365   0.03661  -0.1335   0.2419   1.0000
  11.500   1.6536   0.04678   0.03955  -0.1309   0.2222   1.0000
  11.750   1.6444   0.05022   0.04298  -0.1287   0.2007   1.0000
  12.000   1.6374   0.05360   0.04622  -0.1268   0.1846   1.0000
  12.250   1.6362   0.05668   0.04916  -0.1252   0.1707   1.0000
  12.500   1.6402   0.05937   0.05182  -0.1239   0.1594   1.0000
  12.750   1.6473   0.06176   0.05412  -0.1228   0.1510   1.0000
  13.000   1.6543   0.06416   0.05660  -0.1219   0.1441   1.0000
  13.250   1.6719   0.06569   0.05801  -0.1211   0.1385   1.0000
  13.500   1.6849   0.06775   0.06022  -0.1203   0.1340   1.0000
  13.750   1.7046   0.06920   0.06165  -0.1197   0.1297   1.0000
  14.000   1.7306   0.07045   0.06287  -0.1192   0.1252   1.0000
  14.250   1.7322   0.07342   0.06614  -0.1184   0.1222   1.0000
  14.500   1.7367   0.07606   0.06892  -0.1178   0.1184   1.0000
  14.750   1.7613   0.07718   0.06985  -0.1175   0.1135   1.0000
  15.000   1.7531   0.08093   0.07395  -0.1169   0.1114   1.0000
  15.250   1.7482   0.08452   0.07781  -0.1165   0.1087   1.0000
  15.500   1.7486   0.08752   0.08094  -0.1164   0.1058   1.0000
  15.750   1.7681   0.08865   0.08192  -0.1161   0.1017   1.0000
  16.000   1.7584   0.09294   0.08655  -0.1162   0.1002   1.0000
  16.250   1.7494   0.09726   0.09116  -0.1166   0.0982   1.0000
  16.500   1.7449   0.10115   0.09527  -0.1172   0.0962   1.0000
  16.750   1.7491   0.10372   0.09788  -0.1175   0.0935   1.0000
  17.000   1.7685   0.10485   0.09892  -0.1172   0.0903   1.0000
  17.250   1.7530   0.11023   0.10466  -0.1186   0.0894   1.0000
  17.500   1.7368   0.11597   0.11073  -0.1205   0.0883   1.0000
  17.750   1.7212   0.12191   0.11697  -0.1229   0.0873   1.0000
  18.000   1.7045   0.12826   0.12361  -0.1257   0.0866   1.0000
  18.250   1.6843   0.13543   0.13107  -0.1294   0.0858   1.0000
  18.500   1.6505   0.14570   0.14169  -0.1353   0.0862   1.0000
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