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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 200,000
Max Cl/Cd: 85.38 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-la203a-il-200000-n5.txt
Download as CSV file: xf-la203a-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0371   0.09450   0.08938  -0.0943   0.7630   0.0491
  -9.000  -0.0308   0.09155   0.08640  -0.0961   0.7598   0.0504
  -8.500  -0.0393   0.07948   0.07429  -0.1045   0.7534   0.0407
  -8.250  -0.0291   0.07713   0.07195  -0.1053   0.7495   0.0404
  -8.000  -0.0217   0.07408   0.06890  -0.1071   0.7459   0.0400
  -7.750  -0.0164   0.07047   0.06527  -0.1096   0.7428   0.0395
  -7.500  -0.0130   0.06617   0.06098  -0.1132   0.7394   0.0391
  -7.250  -0.0138   0.06089   0.05573  -0.1185   0.7354   0.0388
  -7.000  -0.0179   0.05064   0.04534  -0.1343   0.7314   0.0388
  -6.750  -0.0132   0.04335   0.03770  -0.1428   0.7281   0.0390
  -6.500  -0.0007   0.03762   0.03156  -0.1479   0.7248   0.0389
  -6.250   0.0175   0.03298   0.02647  -0.1513   0.7212   0.0391
  -6.000   0.0403   0.02941   0.02243  -0.1537   0.7181   0.0394
  -5.750   0.0661   0.02668   0.01924  -0.1554   0.7153   0.0400
  -5.500   0.0938   0.02447   0.01652  -0.1568   0.7127   0.0407
  -5.250   0.1213   0.02337   0.01525  -0.1575   0.7096   0.0414
  -5.000   0.1487   0.02275   0.01459  -0.1580   0.7061   0.0421
  -4.750   0.1766   0.02207   0.01382  -0.1584   0.7030   0.0429
  -4.500   0.2052   0.02124   0.01281  -0.1590   0.7003   0.0436
  -4.250   0.2344   0.02040   0.01177  -0.1595   0.6978   0.0443
  -4.000   0.2629   0.01966   0.01087  -0.1598   0.6948   0.0451
  -3.750   0.2908   0.01902   0.01011  -0.1600   0.6911   0.0459
  -3.500   0.3189   0.01847   0.00949  -0.1602   0.6878   0.0467
  -3.250   0.3474   0.01806   0.00910  -0.1605   0.6848   0.0476
  -3.000   0.3765   0.01775   0.00874  -0.1609   0.6821   0.0490
  -2.750   0.4051   0.01742   0.00837  -0.1611   0.6790   0.0507
  -2.500   0.4330   0.01709   0.00802  -0.1612   0.6752   0.0520
  -2.250   0.4615   0.01673   0.00771  -0.1615   0.6718   0.0532
  -2.000   0.4907   0.01645   0.00745  -0.1619   0.6685   0.0546
  -1.750   0.5206   0.01619   0.00717  -0.1624   0.6657   0.0565
  -1.500   0.5501   0.01600   0.00697  -0.1628   0.6625   0.0590
  -1.250   0.5791   0.01581   0.00687  -0.1633   0.6587   0.0617
  -1.000   0.6088   0.01565   0.00672  -0.1638   0.6550   0.0648
  -0.750   0.6394   0.01546   0.00654  -0.1645   0.6517   0.0680
  -0.500   0.6701   0.01534   0.00639  -0.1651   0.6489   0.0732
  -0.250   0.7006   0.01523   0.00630  -0.1658   0.6458   0.0806
   0.000   0.7303   0.01512   0.00626  -0.1664   0.6416   0.0911
   0.250   0.7613   0.01496   0.00622  -0.1672   0.6378   0.1165
   0.500   0.8038   0.01382   0.00646  -0.1716   0.6345   0.5517
   0.750   0.8328   0.01386   0.00661  -0.1716   0.6315   0.6266
   1.000   0.8603   0.01399   0.00680  -0.1713   0.6279   0.6648
   1.250   0.8864   0.01415   0.00703  -0.1708   0.6236   0.6949
   1.500   0.9133   0.01428   0.00719  -0.1703   0.6196   0.7182
   1.750   0.9398   0.01437   0.00728  -0.1698   0.6161   0.7334
   2.000   0.9681   0.01444   0.00730  -0.1697   0.6131   0.7429
   2.250   0.9944   0.01459   0.00750  -0.1695   0.6086   0.7516
   2.500   1.0216   0.01471   0.00763  -0.1693   0.6041   0.7595
   2.750   1.0485   0.01479   0.00772  -0.1691   0.6002   0.7659
   3.000   1.0775   0.01487   0.00775  -0.1693   0.5968   0.7720
   3.250   1.1048   0.01500   0.00790  -0.1692   0.5927   0.7780
   3.500   1.1302   0.01514   0.00811  -0.1688   0.5878   0.7838
   3.750   1.1575   0.01526   0.00824  -0.1687   0.5835   0.7904
   4.000   1.1855   0.01536   0.00832  -0.1688   0.5800   0.7966
   4.250   1.2114   0.01550   0.00849  -0.1684   0.5758   0.8030
   4.500   1.2370   0.01569   0.00875  -0.1681   0.5706   0.8110
   4.750   1.2623   0.01583   0.00893  -0.1676   0.5660   0.8181
   5.000   1.2891   0.01595   0.00904  -0.1674   0.5622   0.8259
   5.250   1.3143   0.01613   0.00928  -0.1669   0.5576   0.8340
   5.500   1.3373   0.01633   0.00957  -0.1661   0.5521   0.8432
   5.750   1.3617   0.01647   0.00974  -0.1655   0.5471   0.8532
   6.000   1.3868   0.01660   0.00986  -0.1649   0.5428   0.8641
   6.250   1.4065   0.01683   0.01021  -0.1634   0.5363   0.8759
   6.500   1.4274   0.01697   0.01040  -0.1621   0.5300   0.8898
   6.750   1.4466   0.01709   0.01053  -0.1604   0.5236   0.9083
   7.000   1.4590   0.01720   0.01075  -0.1574   0.5152   0.9421
   7.250   1.4797   0.01733   0.01086  -0.1562   0.5063   0.9999
   7.500   1.5012   0.01766   0.01119  -0.1554   0.4946   0.9999
   7.750   1.5207   0.01804   0.01156  -0.1543   0.4820   0.9999
   8.000   1.5386   0.01846   0.01194  -0.1528   0.4689   0.9999
   8.250   1.5531   0.01894   0.01238  -0.1508   0.4557   0.9999
   8.500   1.5664   0.01954   0.01298  -0.1487   0.4420   0.9999
   8.750   1.5784   0.02023   0.01366  -0.1466   0.4281   0.9999
   9.000   1.5889   0.02104   0.01444  -0.1443   0.4142   0.9999
   9.250   1.5974   0.02201   0.01539  -0.1420   0.3995   0.9999
   9.500   1.6042   0.02316   0.01651  -0.1396   0.3841   0.9999
   9.750   1.6091   0.02452   0.01784  -0.1373   0.3675   0.9999
  10.000   1.6122   0.02611   0.01938  -0.1350   0.3497   0.9999
  10.250   1.6134   0.02794   0.02117  -0.1327   0.3306   0.9999
  10.500   1.6119   0.03008   0.02324  -0.1304   0.3095   0.9999
  10.750   1.6073   0.03255   0.02563  -0.1280   0.2876   0.9999
  11.000   1.6006   0.03527   0.02827  -0.1257   0.2652   0.9999
  11.250   1.5926   0.03819   0.03110  -0.1234   0.2434   0.9999
  11.500   1.5840   0.04125   0.03407  -0.1213   0.2234   0.9999
  11.750   1.5758   0.04439   0.03713  -0.1193   0.2051   0.9999
  12.000   1.5691   0.04751   0.04019  -0.1176   0.1879   0.9999
  12.250   1.5633   0.05063   0.04326  -0.1160   0.1722   0.9999
  12.500   1.5582   0.05378   0.04636  -0.1147   0.1574   0.9999
  13.000   1.5508   0.06004   0.05257  -0.1124   0.1321   0.9999
  13.250   1.5483   0.06313   0.05564  -0.1114   0.1211   0.9999
  13.500   1.5459   0.06627   0.05878  -0.1106   0.1117   0.9999
  13.750   1.5431   0.06950   0.06200  -0.1098   0.1034   0.9999
  14.000   1.5422   0.07255   0.06507  -0.1091   0.0956   0.9999
  14.250   1.5409   0.07570   0.06823  -0.1086   0.0891   0.9999
  14.500   1.5390   0.07895   0.07150  -0.1080   0.0832   0.9999
  14.750   1.5389   0.08203   0.07462  -0.1076   0.0779   0.9999
  15.000   1.5371   0.08535   0.07795  -0.1073   0.0734   0.9999
  15.250   1.5373   0.08842   0.08108  -0.1070   0.0693   0.9999
  15.500   1.5363   0.09169   0.08438  -0.1068   0.0657   0.9999
  15.750   1.5357   0.09493   0.08768  -0.1067   0.0626   0.9999
  16.000   1.5361   0.09807   0.09088  -0.1067   0.0597   0.9999
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