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FX 73-CL3-152 (fx73cl3152-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 73-CL3-152 (fx73cl3152-il)
Reynolds number: 50,000
Max Cl/Cd: 28.43 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73cl3152-il-50000-n5.txt
Download as CSV file: xf-fx73cl3152-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-CL3-152                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250   0.0766   0.11068   0.10403  -0.0868   0.8961   0.1274
  -8.000   0.0770   0.11018   0.10354  -0.0916   0.8845   0.1292
  -7.750   0.0990   0.10539   0.09877  -0.0923   0.8735   0.1306
  -7.500   0.1228   0.10132   0.09468  -0.0934   0.8629   0.1330
  -7.250   0.1396   0.09826   0.09160  -0.0950   0.8511   0.1352
  -7.000   0.1463   0.09611   0.08947  -0.0950   0.8349   0.1367
  -6.750   0.1519   0.09404   0.08742  -0.0951   0.8185   0.1381
  -6.500   0.1559   0.09203   0.08542  -0.0948   0.8016   0.1387
  -6.250   0.1587   0.09003   0.08343  -0.0943   0.7842   0.1385
  -5.750   0.1336   0.08326   0.07656  -0.0980   0.7500   0.0925
  -5.500   0.1502   0.08024   0.07347  -0.0988   0.7382   0.0917
  -5.250   0.1607   0.07764   0.07083  -0.0993   0.7241   0.0908
  -5.000   0.1721   0.07492   0.06804  -0.1004   0.7110   0.0892
  -4.750   0.1878   0.07149   0.06449  -0.1036   0.7009   0.0874
  -4.500   0.2010   0.06797   0.06088  -0.1074   0.6891   0.0856
  -4.250   0.2196   0.06445   0.05723  -0.1118   0.6787   0.0855
  -4.000   0.2430   0.06110   0.05372  -0.1163   0.6692   0.0869
  -3.750   0.2685   0.05728   0.04974  -0.1223   0.6595   0.0879
  -3.500   0.3044   0.05190   0.04408  -0.1318   0.6508   0.0882
  -3.250   0.3568   0.04415   0.03570  -0.1470   0.6428   0.0908
  -3.000   0.3978   0.04023   0.03126  -0.1542   0.6336   0.0944
  -2.750   0.4370   0.03778   0.02837  -0.1583   0.6263   0.0977
  -2.500   0.4736   0.03513   0.02503  -0.1627   0.6172   0.1038
  -2.250   0.5050   0.03439   0.02414  -0.1636   0.6104   0.1085
  -2.000   0.5373   0.03309   0.02231  -0.1654   0.6033   0.1155
  -1.750   0.5637   0.03280   0.02202  -0.1654   0.5961   0.1219
  -1.500   0.5975   0.03196   0.02080  -0.1666   0.5904   0.1316
  -1.250   0.6232   0.03176   0.02047  -0.1665   0.5838   0.1418
  -1.000   0.6489   0.03164   0.02030  -0.1664   0.5773   0.1538
  -0.750   0.6802   0.03138   0.01987  -0.1670   0.5722   0.1708
  -0.500   0.7104   0.03133   0.01967  -0.1674   0.5674   0.1919
  -0.250   0.7339   0.03162   0.01990  -0.1671   0.5615   0.2143
   0.000   0.7613   0.03180   0.02005  -0.1671   0.5563   0.2400
   0.250   0.7922   0.03188   0.02004  -0.1675   0.5520   0.2699
   0.500   0.8188   0.03220   0.02026  -0.1674   0.5474   0.2983
   0.750   0.8390   0.03276   0.02090  -0.1665   0.5420   0.3222
   1.000   0.8644   0.03314   0.02126  -0.1662   0.5374   0.3489
   1.250   0.8941   0.03337   0.02137  -0.1664   0.5337   0.3793
   1.500   0.9260   0.03350   0.02142  -0.1668   0.5304   0.4103
   1.750   0.9385   0.03451   0.02258  -0.1651   0.5250   0.4354
   2.000   0.9580   0.03520   0.02334  -0.1641   0.5203   0.4648
   2.250   0.9831   0.03563   0.02380  -0.1637   0.5164   0.5015
   2.500   1.0122   0.03588   0.02403  -0.1637   0.5132   0.5448
   2.750   1.0355   0.03642   0.02462  -0.1631   0.5098   0.5911
   3.000   1.0401   0.03785   0.02628  -0.1605   0.5044   0.6309
   3.250   1.0556   0.03866   0.02724  -0.1590   0.5001   0.6908
   3.500   1.0731   0.03870   0.02752  -0.1573   0.4965   1.0000
   3.750   1.1065   0.03917   0.02769  -0.1583   0.4937   1.0000
   4.000   1.1185   0.04069   0.02913  -0.1569   0.4896   1.0000
   4.250   1.1032   0.04360   0.03217  -0.1527   0.4834   1.0000
   4.500   1.1144   0.04511   0.03359  -0.1512   0.4791   1.0000
   4.750   1.1412   0.04576   0.03409  -0.1511   0.4761   1.0000
   5.000   1.1760   0.04602   0.03415  -0.1518   0.4737   1.0000
   5.250   1.0606   0.05601   0.04467  -0.1411   0.4610   1.0000
   5.500   1.0816   0.05702   0.04557  -0.1405   0.4578   1.0000
   5.750   1.1121   0.05723   0.04563  -0.1404   0.4557   1.0000
   6.000   1.1486   0.05703   0.04529  -0.1407   0.4541   1.0000
   7.500   0.9816   0.09615   0.08502  -0.1365   0.4046   1.0000
   7.750   0.9978   0.09793   0.08676  -0.1361   0.4019   1.0000
   8.000   1.0197   0.09899   0.08774  -0.1356   0.3998   1.0000
   8.500   0.9930   0.10966   0.09854  -0.1365   0.3868   1.0000
   8.750   1.0077   0.11166   0.10050  -0.1363   0.3842   1.0000
   9.000   1.0272   0.11309   0.10190  -0.1359   0.3822   1.0000
   9.250   1.0046   0.11965   0.10856  -0.1370   0.3754   1.0000
   9.500   1.0070   0.12305   0.11199  -0.1373   0.3708   1.0000
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