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EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1230 AIRFOIL (e1230-il)
Reynolds number: 50,000
Max Cl/Cd: 24.91 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1230-il-50000-n5.txt
Download as CSV file: xf-e1230-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1230 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4573   0.07762   0.07048  -0.0627   1.0000   0.0517
 -10.250  -0.4859   0.07260   0.06544  -0.0638   1.0000   0.0514
 -10.000  -0.5158   0.06870   0.06151  -0.0631   1.0000   0.0512
  -9.750  -0.5462   0.06587   0.05865  -0.0601   1.0000   0.0510
  -9.500  -0.5723   0.06298   0.05567  -0.0567   1.0000   0.0509
  -9.250  -0.5941   0.06007   0.05264  -0.0532   1.0000   0.0510
  -9.000  -0.6126   0.05726   0.04964  -0.0496   1.0000   0.0512
  -8.750  -0.6284   0.05450   0.04661  -0.0459   1.0000   0.0516
  -8.500  -0.6369   0.05227   0.04420  -0.0426   1.0000   0.0523
  -8.250  -0.6369   0.05104   0.04297  -0.0398   1.0000   0.0534
  -8.000  -0.6084   0.04837   0.04002  -0.0428   0.9901   0.0562
  -7.750  -0.5810   0.04459   0.03554  -0.0453   0.9787   0.0594
  -7.500  -0.5470   0.04259   0.03348  -0.0479   0.9670   0.0621
  -7.250  -0.5163   0.04027   0.03075  -0.0495   0.9533   0.0668
  -7.000  -0.4835   0.03862   0.02905  -0.0513   0.9397   0.0717
  -6.750  -0.4492   0.03674   0.02691  -0.0529   0.9267   0.0784
  -6.500  -0.4133   0.03523   0.02520  -0.0547   0.9142   0.0873
  -6.250  -0.3749   0.03380   0.02375  -0.0568   0.9027   0.0987
  -6.000  -0.3414   0.03255   0.02246  -0.0580   0.8887   0.1123
  -5.750  -0.3068   0.03134   0.02123  -0.0593   0.8754   0.1288
  -5.500  -0.2708   0.03010   0.02007  -0.0609   0.8632   0.1483
  -5.250  -0.2359   0.02893   0.01892  -0.0622   0.8502   0.1713
  -5.000  -0.2065   0.02792   0.01793  -0.0626   0.8348   0.1968
  -4.750  -0.1787   0.02685   0.01700  -0.0628   0.8198   0.2278
  -4.500  -0.1513   0.02572   0.01607  -0.0629   0.8055   0.2729
  -4.250  -0.1259   0.02452   0.01533  -0.0626   0.7920   0.3491
  -4.000  -0.1073   0.02403   0.01551  -0.0600   0.7761   0.4579
  -3.750  -0.0847   0.02429   0.01594  -0.0574   0.7609   0.5514
  -3.500  -0.0612   0.02459   0.01603  -0.0554   0.7466   0.6079
  -3.250  -0.0362   0.02484   0.01603  -0.0536   0.7335   0.6477
  -3.000  -0.0165   0.02501   0.01601  -0.0513   0.7184   0.6787
  -2.750   0.0068   0.02515   0.01598  -0.0493   0.7048   0.7055
  -2.500   0.0336   0.02523   0.01586  -0.0476   0.6929   0.7319
  -2.250   0.0563   0.02536   0.01590  -0.0454   0.6793   0.7559
  -2.000   0.0821   0.02552   0.01593  -0.0436   0.6669   0.7792
  -1.750   0.1097   0.02557   0.01577  -0.0423   0.6559   0.8013
  -1.500   0.1348   0.02570   0.01578  -0.0411   0.6429   0.8182
  -1.250   0.1667   0.02576   0.01565  -0.0412   0.6320   0.8315
  -1.000   0.1963   0.02582   0.01554  -0.0412   0.6204   0.8428
  -0.750   0.2239   0.02587   0.01544  -0.0411   0.6092   0.8536
  -0.500   0.2553   0.02590   0.01527  -0.0417   0.5991   0.8634
  -0.250   0.2856   0.02605   0.01530  -0.0423   0.5881   0.8721
   0.000   0.3173   0.02606   0.01512  -0.0430   0.5791   0.8810
   0.250   0.3411   0.02622   0.01521  -0.0427   0.5685   0.8914
   0.500   0.3758   0.02628   0.01507  -0.0441   0.5600   0.8993
   0.750   0.4045   0.02651   0.01525  -0.0449   0.5500   0.9081
   1.000   0.4376   0.02661   0.01519  -0.0461   0.5418   0.9167
   1.250   0.4709   0.02689   0.01542  -0.0477   0.5324   0.9246
   1.500   0.5057   0.02708   0.01549  -0.0494   0.5242   0.9332
   1.750   0.5377   0.02735   0.01568  -0.0509   0.5163   0.9433
   2.000   0.5725   0.02766   0.01593  -0.0529   0.5077   0.9526
   2.250   0.6118   0.02782   0.01593  -0.0555   0.5012   0.9613
   2.500   0.6429   0.02833   0.01651  -0.0573   0.4923   0.9733
   2.750   0.6800   0.02858   0.01665  -0.0597   0.4857   0.9848
   3.000   0.7145   0.02903   0.01709  -0.0620   0.4785   0.9987
   3.250   0.7192   0.02945   0.01752  -0.0590   0.4724   1.0000
   3.500   0.7300   0.02972   0.01770  -0.0567   0.4674   1.0000
   3.750   0.7438   0.03011   0.01798  -0.0549   0.4627   1.0000
   4.000   0.7495   0.03093   0.01886  -0.0520   0.4563   1.0000
   4.250   0.7667   0.03147   0.01933  -0.0507   0.4510   1.0000
   4.500   0.7915   0.03180   0.01951  -0.0504   0.4467   1.0000
   4.750   0.8004   0.03282   0.02060  -0.0481   0.4406   1.0000
   5.000   0.8144   0.03369   0.02148  -0.0466   0.4349   1.0000
   5.250   0.8373   0.03421   0.02194  -0.0460   0.4305   1.0000
   5.500   0.8635   0.03466   0.02228  -0.0460   0.4268   1.0000
   5.750   0.8624   0.03634   0.02414  -0.0428   0.4204   1.0000
   6.000   0.8769   0.03731   0.02513  -0.0414   0.4153   1.0000
   6.250   0.9021   0.03779   0.02556  -0.0412   0.4114   1.0000
   6.500   0.9207   0.03867   0.02643  -0.0404   0.4075   1.0000
   6.750   0.9084   0.04114   0.02910  -0.0365   0.4013   1.0000
   7.000   0.9180   0.04249   0.03048  -0.0349   0.3967   1.0000
   7.250   0.9433   0.04299   0.03097  -0.0347   0.3933   1.0000
   7.500   0.9597   0.04404   0.03202  -0.0338   0.3896   1.0000
   7.750   0.8906   0.05017   0.03841  -0.0265   0.3808   1.0000
   8.000   0.9001   0.05179   0.04006  -0.0256   0.3769   1.0000
   8.250   0.9292   0.05201   0.04026  -0.0255   0.3744   1.0000
   8.750   0.8371   0.06675   0.05523  -0.0238   0.3569   1.0000
   9.000   0.8666   0.06642   0.05490  -0.0230   0.3553   1.0000
  10.500   0.7555   0.10187   0.09069  -0.0296   0.3148   1.0000
  10.750   0.7549   0.10545   0.09432  -0.0302   0.3098   1.0000
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