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EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 407 AIRFOIL (e407-il)
Reynolds number: 500,000
Max Cl/Cd: 112.99 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e407-il-500000.txt
Download as CSV file: xf-e407-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 407 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2561   0.08756   0.08534  -0.0949   0.9727   0.0200
 -11.500  -0.2647   0.07935   0.07713  -0.0989   0.9722   0.0202
 -11.250  -0.3187   0.06152   0.05911  -0.1102   0.9715   0.0199
 -11.000  -0.3417   0.05363   0.05107  -0.1160   0.9707   0.0197
  -9.250  -0.4987   0.03742   0.03336  -0.1216   0.9448   0.0143
  -9.000  -0.5280   0.02984   0.02506  -0.1134   0.9361   0.0079
  -8.750  -0.5098   0.02694   0.02181  -0.1136   0.9343   0.0076
  -8.500  -0.4856   0.02481   0.01942  -0.1142   0.9331   0.0074
  -8.250  -0.4600   0.02315   0.01755  -0.1148   0.9322   0.0075
  -8.000  -0.4325   0.02182   0.01609  -0.1158   0.9314   0.0076
  -7.750  -0.4369   0.02133   0.01553  -0.1104   0.9235   0.0076
  -7.500  -0.4109   0.02028   0.01438  -0.1111   0.9218   0.0081
  -7.250  -0.3821   0.01929   0.01330  -0.1123   0.9206   0.0084
  -7.000  -0.3508   0.01847   0.01239  -0.1139   0.9197   0.0090
  -6.750  -0.3186   0.01718   0.01102  -0.1163   0.9189   0.0110
  -6.500  -0.2841   0.01652   0.01030  -0.1184   0.9183   0.0129
  -6.250  -0.2764   0.01612   0.00988  -0.1153   0.9119   0.0171
  -6.000  -0.2458   0.01541   0.00920  -0.1168   0.9100   0.0301
  -5.750  -0.2121   0.01480   0.00870  -0.1188   0.9088   0.0511
  -5.500  -0.1766   0.01406   0.00818  -0.1215   0.9080   0.0980
  -5.250  -0.1389   0.01314   0.00764  -0.1249   0.9074   0.1863
  -5.000  -0.0973   0.01190   0.00700  -0.1297   0.9072   0.3334
  -4.750  -0.0564   0.01106   0.00670  -0.1336   0.9069   0.4823
  -4.500  -0.0202   0.01093   0.00659  -0.1355   0.9063   0.5221
  -4.250   0.0163   0.01087   0.00649  -0.1374   0.9058   0.5467
  -4.000   0.0530   0.01087   0.00648  -0.1392   0.9054   0.5666
  -3.750   0.0899   0.01085   0.00641  -0.1411   0.9049   0.5784
  -3.500   0.1267   0.01085   0.00632  -0.1430   0.9044   0.5885
  -3.250   0.1335   0.01116   0.00666  -0.1388   0.8970   0.5940
  -3.000   0.1674   0.01115   0.00660  -0.1401   0.8956   0.6018
  -2.750   0.2023   0.01111   0.00653  -0.1415   0.8946   0.6074
  -2.500   0.2384   0.01105   0.00646  -0.1432   0.8936   0.6134
  -2.250   0.2754   0.01095   0.00630  -0.1452   0.8928   0.6192
  -2.000   0.3116   0.01086   0.00623  -0.1468   0.8919   0.6242
  -1.750   0.3493   0.01079   0.00612  -0.1488   0.8911   0.6310
  -1.500   0.3861   0.01064   0.00597  -0.1507   0.8902   0.6346
  -1.250   0.3996   0.01079   0.00614  -0.1478   0.8833   0.6369
  -1.000   0.4341   0.01062   0.00597  -0.1492   0.8812   0.6395
  -0.750   0.4713   0.01041   0.00573  -0.1512   0.8794   0.6424
  -0.500   0.5092   0.01019   0.00548  -0.1533   0.8778   0.6454
  -0.250   0.5476   0.00998   0.00525  -0.1556   0.8763   0.6479
   0.000   0.5663   0.01001   0.00533  -0.1537   0.8699   0.6499
   0.250   0.5984   0.00986   0.00519  -0.1546   0.8665   0.6521
   0.500   0.6351   0.00965   0.00498  -0.1564   0.8638   0.6546
   0.750   0.6646   0.00955   0.00489  -0.1568   0.8592   0.6574
   1.000   0.6914   0.00947   0.00481  -0.1567   0.8535   0.6601
   1.250   0.7267   0.00928   0.00462  -0.1582   0.8497   0.6624
   1.500   0.7512   0.00922   0.00462  -0.1575   0.8434   0.6645
   1.750   0.7810   0.00909   0.00451  -0.1578   0.8372   0.6666
   2.000   0.8081   0.00900   0.00446  -0.1577   0.8299   0.6690
   2.250   0.8370   0.00891   0.00437  -0.1578   0.8223   0.6717
   2.500   0.8622   0.00888   0.00435  -0.1573   0.8133   0.6746
   2.750   0.8911   0.00879   0.00428  -0.1575   0.8042   0.6769
   3.000   0.9177   0.00873   0.00425  -0.1572   0.7926   0.6788
   3.250   0.9419   0.00872   0.00426  -0.1564   0.7786   0.6810
   3.500   0.9651   0.00875   0.00430  -0.1553   0.7622   0.6836
   3.750   0.9880   0.00882   0.00435  -0.1543   0.7419   0.6864
   4.000   1.0101   0.00894   0.00440  -0.1530   0.7152   0.6892
   4.250   1.0285   0.00916   0.00448  -0.1510   0.6807   0.6914
   4.500   1.0423   0.00946   0.00465  -0.1481   0.6422   0.6935
   4.750   1.0508   0.00987   0.00489  -0.1441   0.6007   0.6959
   5.000   1.0586   0.01038   0.00522  -0.1401   0.5579   0.6987
   5.250   1.0672   0.01098   0.00562  -0.1364   0.5139   0.7016
   5.500   1.0780   0.01159   0.00604  -0.1333   0.4714   0.7044
   5.750   1.0877   0.01225   0.00650  -0.1301   0.4262   0.7066
   6.000   1.0983   0.01296   0.00701  -0.1271   0.3796   0.7089
   6.250   1.1114   0.01362   0.00751  -0.1246   0.3394   0.7115
   6.500   1.1251   0.01432   0.00805  -0.1224   0.3008   0.7145
   6.750   1.1389   0.01509   0.00861  -0.1202   0.2594   0.7176
   7.000   1.1533   0.01584   0.00917  -0.1182   0.2202   0.7203
   7.250   1.1680   0.01657   0.00977  -0.1163   0.1878   0.7227
   7.500   1.1836   0.01729   0.01037  -0.1146   0.1587   0.7254
   7.750   1.1987   0.01807   0.01102  -0.1128   0.1307   0.7284
   8.250   1.2300   0.01961   0.01239  -0.1095   0.0869   0.7346
   8.500   1.2443   0.02046   0.01316  -0.1077   0.0689   0.7374
   8.750   1.2589   0.02131   0.01397  -0.1060   0.0543   0.7404
   9.000   1.2732   0.02222   0.01484  -0.1042   0.0428   0.7437
   9.250   1.2861   0.02327   0.01586  -0.1023   0.0341   0.7469
   9.500   1.3022   0.02403   0.01669  -0.1008   0.0296   0.7499
   9.750   1.3115   0.02534   0.01803  -0.0984   0.0245   0.7530
  10.000   1.3281   0.02605   0.01884  -0.0971   0.0224   0.7568
  10.250   1.3423   0.02702   0.01986  -0.0956   0.0200   0.7607
  10.500   1.3468   0.02876   0.02169  -0.0928   0.0173   0.7639
  10.750   1.3627   0.02954   0.02259  -0.0916   0.0162   0.7675
  11.000   1.3772   0.03048   0.02360  -0.0902   0.0145   0.7714
  11.250   1.3872   0.03183   0.02499  -0.0885   0.0128   0.7756
  11.500   1.3913   0.03369   0.02698  -0.0861   0.0115   0.7793
  11.750   1.4030   0.03488   0.02830  -0.0846   0.0105   0.7837
  12.000   1.4133   0.03626   0.02975  -0.0831   0.0096   0.7886
  12.250   1.4195   0.03800   0.03158  -0.0813   0.0087   0.7931
  12.500   1.4113   0.04123   0.03499  -0.0783   0.0079   0.7969
  12.750   1.4202   0.04287   0.03676  -0.0770   0.0075   0.8023
  13.000   1.4260   0.04486   0.03893  -0.0756   0.0070   0.8074
  13.250   1.4308   0.04697   0.04118  -0.0742   0.0066   0.8132
  13.500   1.4353   0.04920   0.04352  -0.0731   0.0062   0.8199
  13.750   1.4385   0.05158   0.04603  -0.0720   0.0059   0.8268
  14.000   1.4375   0.05457   0.04915  -0.0710   0.0056   0.8344
  14.250   1.4272   0.05884   0.05362  -0.0698   0.0053   0.8412
  14.500   1.4195   0.06306   0.05806  -0.0690   0.0051   0.8493
  14.750   1.4211   0.06605   0.06124  -0.0688   0.0050   0.8617
  15.000   1.4201   0.06939   0.06478  -0.0686   0.0048   0.8783
  15.500   1.4067   0.07659   0.07238  -0.0676   0.0046   1.0000
  15.750   1.4020   0.08119   0.07714  -0.0687   0.0044   1.0000
  16.000   1.3969   0.08601   0.08211  -0.0701   0.0043   1.0000
  16.250   1.3889   0.09145   0.08771  -0.0719   0.0042   1.0000
  16.500   1.3801   0.09721   0.09363  -0.0741   0.0042   1.0000
  16.750   1.3696   0.10349   0.10008  -0.0768   0.0041   1.0000
  17.000   1.3587   0.11003   0.10679  -0.0799   0.0041   1.0000
  17.250   1.3466   0.11699   0.11393  -0.0835   0.0041   1.0000
  17.500   1.3338   0.12429   0.12139  -0.0876   0.0040   1.0000
  17.750   1.3208   0.13186   0.12912  -0.0920   0.0040   1.0000
  18.000   1.3063   0.13996   0.13740  -0.0970   0.0040   1.0000
  18.250   1.2912   0.14847   0.14608  -0.1024   0.0041   1.0000
  18.500   1.2750   0.15751   0.15530  -0.1084   0.0041   1.0000
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