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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 500,000
Max Cl/Cd: 127.74 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-la203a-il-500000.txt
Download as CSV file: xf-la203a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DOUGLAS LA203A 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0532   0.09706   0.09334  -0.0916   0.7620   0.0383
  -9.500  -0.0459   0.09419   0.09043  -0.0932   0.7588   0.0391
  -9.250  -0.0655   0.08572   0.08197  -0.1033   0.7560   0.0410
  -9.000  -0.0559   0.08293   0.07921  -0.1032   0.7528   0.0412
  -8.750  -0.0439   0.08089   0.07717  -0.1033   0.7493   0.0414
  -8.500  -0.0321   0.07885   0.07511  -0.1038   0.7461   0.0416
  -8.250  -0.0209   0.07670   0.07294  -0.1046   0.7430   0.0419
  -8.000  -0.0105   0.07433   0.07057  -0.1059   0.7401   0.0423
  -7.750  -0.0013   0.07163   0.06790  -0.1077   0.7368   0.0428
  -7.500  -0.0368   0.05233   0.04845  -0.1381   0.7330   0.0465
  -7.250  -0.0211   0.05038   0.04651  -0.1387   0.7300   0.0468
  -7.000  -0.0048   0.04843   0.04452  -0.1402   0.7272   0.0470
  -6.750   0.0121   0.04631   0.04237  -0.1422   0.7240   0.0473
  -6.500   0.0298   0.04397   0.03998  -0.1446   0.7207   0.0478
  -6.250   0.0487   0.04136   0.03726  -0.1474   0.7176   0.0487
  -6.000   0.0664   0.03368   0.02887  -0.1555   0.7149   0.0528
  -5.750   0.0906   0.03217   0.02732  -0.1564   0.7121   0.0532
  -5.500   0.1152   0.03082   0.02595  -0.1573   0.7090   0.0538
  -5.250   0.1434   0.02263   0.01675  -0.1618   0.7061   0.0456
  -5.000   0.1716   0.02051   0.01440  -0.1629   0.7031   0.0446
  -4.750   0.2010   0.01865   0.01224  -0.1640   0.7003   0.0441
  -4.500   0.2310   0.01742   0.01076  -0.1648   0.6975   0.0442
  -4.250   0.2601   0.01649   0.00969  -0.1653   0.6945   0.0445
  -4.000   0.2890   0.01574   0.00883  -0.1656   0.6912   0.0450
  -3.750   0.3183   0.01517   0.00814  -0.1659   0.6880   0.0456
  -3.500   0.3482   0.01490   0.00774  -0.1663   0.6850   0.0463
  -3.250   0.3770   0.01410   0.00694  -0.1668   0.6822   0.0474
  -3.000   0.4061   0.01378   0.00662  -0.1671   0.6792   0.0483
  -2.750   0.4350   0.01343   0.00629  -0.1673   0.6760   0.0493
  -2.500   0.4643   0.01311   0.00597  -0.1677   0.6727   0.0503
  -2.250   0.4941   0.01283   0.00566  -0.1680   0.6695   0.0514
  -2.000   0.5242   0.01255   0.00534  -0.1685   0.6667   0.0525
  -1.750   0.5550   0.01226   0.00506  -0.1693   0.6638   0.0543
  -1.500   0.5846   0.01206   0.00492  -0.1697   0.6606   0.0564
  -1.250   0.6147   0.01190   0.00476  -0.1702   0.6572   0.0584
  -1.000   0.6461   0.01160   0.00449  -0.1710   0.6539   0.0609
  -0.750   0.6769   0.01146   0.00435  -0.1717   0.6509   0.0638
  -0.500   0.7084   0.01136   0.00421  -0.1724   0.6478   0.0676
  -0.250   0.7384   0.01125   0.00416  -0.1729   0.6445   0.0731
   0.000   0.7692   0.01111   0.00407  -0.1736   0.6409   0.0815
   0.250   0.8013   0.01089   0.00394  -0.1745   0.6373   0.1030
   0.500   0.8482   0.00967   0.00402  -0.1800   0.6340   0.5820
   0.750   0.8786   0.00976   0.00415  -0.1804   0.6306   0.6339
   1.000   0.9075   0.00982   0.00426  -0.1805   0.6271   0.6600
   1.250   0.9363   0.00988   0.00437  -0.1805   0.6232   0.6806
   1.500   0.9650   0.00995   0.00445  -0.1805   0.6194   0.6986
   1.750   0.9933   0.01002   0.00454  -0.1804   0.6159   0.7125
   2.000   1.0219   0.01015   0.00465  -0.1804   0.6122   0.7253
   2.250   1.0501   0.01024   0.00477  -0.1804   0.6084   0.7377
   2.500   1.0778   0.01027   0.00486  -0.1803   0.6044   0.7455
   2.750   1.1065   0.01034   0.00491  -0.1804   0.6006   0.7518
   3.000   1.1359   0.01045   0.00496  -0.1807   0.5967   0.7574
   3.250   1.1636   0.01051   0.00507  -0.1807   0.5927   0.7629
   3.500   1.1915   0.01058   0.00518  -0.1806   0.5884   0.7698
   3.750   1.2200   0.01066   0.00527  -0.1808   0.5842   0.7768
   4.000   1.2478   0.01075   0.00535  -0.1808   0.5802   0.7823
   4.250   1.2757   0.01087   0.00549  -0.1808   0.5758   0.7887
   4.500   1.3035   0.01095   0.00562  -0.1808   0.5710   0.7954
   4.750   1.3304   0.01102   0.00573  -0.1806   0.5662   0.8016
   5.000   1.3581   0.01117   0.00583  -0.1806   0.5614   0.8086
   5.250   1.3847   0.01126   0.00600  -0.1804   0.5559   0.8157
   5.500   1.4105   0.01133   0.00612  -0.1800   0.5494   0.8233
   5.750   1.4369   0.01150   0.00623  -0.1798   0.5424   0.8320
   6.000   1.4611   0.01155   0.00638  -0.1790   0.5340   0.8403
   6.250   1.4857   0.01172   0.00650  -0.1784   0.5247   0.8499
   6.500   1.5086   0.01181   0.00666  -0.1775   0.5141   0.8596
   6.750   1.5314   0.01199   0.00685  -0.1766   0.5040   0.8707
   7.000   1.5532   0.01219   0.00706  -0.1755   0.4935   0.8838
   7.250   1.5740   0.01236   0.00728  -0.1741   0.4841   0.8983
   7.500   1.5913   0.01259   0.00751  -0.1721   0.4745   0.9164
   7.750   1.6021   0.01265   0.00767  -0.1686   0.4657   0.9511
   8.000   1.6202   0.01293   0.00791  -0.1670   0.4555   0.9999
   8.250   1.6436   0.01328   0.00826  -0.1665   0.4438   0.9999
   8.500   1.6644   0.01370   0.00865  -0.1656   0.4319   0.9999
   8.750   1.6804   0.01420   0.00911  -0.1637   0.4189   0.9999
   9.000   1.6938   0.01481   0.00967  -0.1615   0.4044   0.9999
   9.250   1.7062   0.01548   0.01030  -0.1592   0.3887   0.9999
   9.500   1.7161   0.01630   0.01107  -0.1567   0.3719   0.9999
  10.000   1.7266   0.01865   0.01329  -0.1510   0.3320   0.9999
  10.250   1.7258   0.02041   0.01494  -0.1479   0.3066   0.9999
  10.500   1.7206   0.02267   0.01707  -0.1447   0.2783   0.9999
  10.750   1.7120   0.02538   0.01963  -0.1416   0.2506   0.9999
  11.000   1.7038   0.02819   0.02231  -0.1388   0.2246   0.9999
  11.250   1.6951   0.03112   0.02512  -0.1361   0.2021   0.9999
  11.500   1.6877   0.03398   0.02789  -0.1336   0.1810   0.9999
  11.750   1.6805   0.03688   0.03071  -0.1312   0.1626   0.9999
  12.000   1.6744   0.03976   0.03352  -0.1291   0.1467   0.9999
  12.250   1.6693   0.04263   0.03633  -0.1272   0.1325   0.9999
  12.500   1.6652   0.04548   0.03914  -0.1254   0.1199   0.9999
  12.750   1.6620   0.04834   0.04197  -0.1238   0.1085   0.9999
  13.000   1.6597   0.05115   0.04475  -0.1224   0.0987   0.9999
  13.250   1.6571   0.05408   0.04766  -0.1211   0.0903   0.9999
  13.500   1.6543   0.05709   0.05066  -0.1198   0.0828   0.9999
  13.750   1.6547   0.05980   0.05338  -0.1188   0.0766   0.9999
  14.000   1.6526   0.06282   0.05641  -0.1177   0.0713   0.9999
  14.250   1.6523   0.06568   0.05928  -0.1168   0.0668   0.9999
  14.500   1.6508   0.06874   0.06237  -0.1160   0.0630   0.9999
  14.750   1.6514   0.07158   0.06526  -0.1152   0.0597   0.9999
  15.000   1.6478   0.07496   0.06864  -0.1145   0.0568   0.9999
  15.250   1.6493   0.07774   0.07150  -0.1139   0.0544   0.9999
  15.500   1.6491   0.08078   0.07457  -0.1134   0.0521   0.9999
  15.750   1.6448   0.08436   0.07818  -0.1129   0.0501   0.9999
  16.000   1.6455   0.08732   0.08121  -0.1125   0.0484   0.9999
  16.250   1.6459   0.09034   0.08431  -0.1122   0.0468   0.9999
  16.500   1.6445   0.09359   0.08759  -0.1119   0.0452   0.9999
  16.750   1.6392   0.09740   0.09144  -0.1118   0.0439   0.9999
  17.000   1.6390   0.10057   0.09467  -0.1117   0.0426   0.9999
  17.250   1.6395   0.10367   0.09785  -0.1117   0.0415   0.9999
  17.500   1.6398   0.10678   0.10103  -0.1117   0.0403   0.9999
  17.750   1.6372   0.11032   0.10461  -0.1120   0.0392   0.9999
  18.000   1.6321   0.11418   0.10850  -0.1123   0.0382   0.9999
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