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EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 580 AIRFOIL (e580-il)
Reynolds number: 1,000,000
Max Cl/Cd: 131.45 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e580-il-1000000.txt
Download as CSV file: xf-e580-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 580 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2820   0.08641   0.08473  -0.0876   0.9867   0.0160
 -11.000  -0.3596   0.05739   0.05543  -0.1121   0.9845   0.0159
 -10.750  -0.3807   0.05021   0.04807  -0.1189   0.9791   0.0160
 -10.500  -0.3797   0.04583   0.04358  -0.1246   0.9754   0.0161
 -10.250  -0.3762   0.04100   0.03855  -0.1318   0.9727   0.0162
  -9.250  -0.3563   0.02353   0.01954  -0.1430   0.9462   0.0156
  -9.000  -0.3409   0.02238   0.01819  -0.1416   0.9366   0.0154
  -8.750  -0.3072   0.02103   0.01669  -0.1440   0.9333   0.0153
  -8.500  -0.2809   0.01981   0.01534  -0.1447   0.9256   0.0152
  -8.250  -0.2468   0.01863   0.01403  -0.1468   0.9198   0.0151
  -8.000  -0.2165   0.01747   0.01274  -0.1481   0.9112   0.0151
  -7.750  -0.1842   0.01625   0.01140  -0.1496   0.9025   0.0151
  -7.500  -0.1559   0.01542   0.01046  -0.1502   0.8911   0.0151
  -7.250  -0.1307   0.01431   0.00925  -0.1501   0.8788   0.0151
  -7.000  -0.1079   0.01321   0.00806  -0.1497   0.8662   0.0154
  -6.750  -0.0848   0.01240   0.00718  -0.1494   0.8538   0.0158
  -6.500  -0.0604   0.01184   0.00655  -0.1493   0.8417   0.0161
  -6.250  -0.0357   0.01138   0.00602  -0.1492   0.8296   0.0164
  -6.000  -0.0103   0.01098   0.00555  -0.1491   0.8179   0.0169
  -5.750   0.0157   0.01062   0.00512  -0.1492   0.8069   0.0173
  -5.500   0.0420   0.01031   0.00472  -0.1493   0.7960   0.0177
  -5.250   0.0688   0.01002   0.00436  -0.1494   0.7849   0.0181
  -5.000   0.0959   0.00976   0.00403  -0.1495   0.7746   0.0186
  -4.750   0.1231   0.00954   0.00373  -0.1497   0.7644   0.0189
  -4.500   0.1506   0.00935   0.00347  -0.1498   0.7540   0.0193
  -4.250   0.1785   0.00907   0.00311  -0.1501   0.7442   0.0203
  -4.000   0.2062   0.00890   0.00286  -0.1503   0.7345   0.0221
  -3.750   0.2343   0.00876   0.00268  -0.1505   0.7248   0.0237
  -3.500   0.2623   0.00864   0.00251  -0.1507   0.7158   0.0274
  -3.250   0.2920   0.00810   0.00224  -0.1518   0.7064   0.1114
  -3.000   0.3254   0.00680   0.00176  -0.1546   0.6978   0.3751
  -2.750   0.3546   0.00654   0.00174  -0.1553   0.6889   0.4743
  -2.500   0.3832   0.00656   0.00175  -0.1555   0.6806   0.4982
  -2.250   0.4109   0.00665   0.00180  -0.1555   0.6723   0.5155
  -2.000   0.4394   0.00675   0.00186  -0.1556   0.6643   0.5300
  -1.750   0.4669   0.00691   0.00199  -0.1555   0.6564   0.5436
  -1.500   0.4952   0.00696   0.00202  -0.1556   0.6487   0.5498
  -1.250   0.5226   0.00708   0.00208  -0.1555   0.6412   0.5547
  -1.000   0.5510   0.00715   0.00212  -0.1556   0.6340   0.5593
  -0.750   0.5786   0.00725   0.00214  -0.1556   0.6267   0.5612
  -0.500   0.6068   0.00725   0.00213  -0.1558   0.6201   0.5636
  -0.250   0.6345   0.00730   0.00214  -0.1558   0.6131   0.5656
   0.000   0.6623   0.00736   0.00218  -0.1559   0.6067   0.5677
   0.250   0.6902   0.00741   0.00221  -0.1559   0.6000   0.5697
   0.500   0.7175   0.00750   0.00225  -0.1559   0.5936   0.5717
   0.750   0.7456   0.00755   0.00228  -0.1560   0.5873   0.5736
   1.000   0.7729   0.00764   0.00233  -0.1560   0.5808   0.5756
   1.250   0.8007   0.00771   0.00238  -0.1560   0.5747   0.5772
   1.500   0.8281   0.00775   0.00241  -0.1561   0.5682   0.5795
   1.750   0.8551   0.00783   0.00247  -0.1560   0.5620   0.5815
   2.000   0.8828   0.00788   0.00253  -0.1560   0.5558   0.5834
   2.250   0.9094   0.00799   0.00262  -0.1559   0.5491   0.5856
   2.500   0.9369   0.00806   0.00269  -0.1559   0.5430   0.5877
   2.750   0.9636   0.00816   0.00276  -0.1558   0.5360   0.5899
   3.000   0.9904   0.00826   0.00285  -0.1556   0.5295   0.5918
   3.250   1.0172   0.00835   0.00293  -0.1556   0.5225   0.5933
   3.500   1.0432   0.00845   0.00302  -0.1553   0.5155   0.5959
   3.750   1.0700   0.00852   0.00312  -0.1552   0.5081   0.5983
   4.000   1.0954   0.00866   0.00324  -0.1549   0.5004   0.6006
   4.250   1.1218   0.00875   0.00335  -0.1547   0.4922   0.6029
   4.500   1.1469   0.00890   0.00347  -0.1543   0.4836   0.6051
   4.750   1.1723   0.00903   0.00360  -0.1539   0.4745   0.6073
   5.000   1.1974   0.00918   0.00373  -0.1535   0.4655   0.6092
   5.500   1.2461   0.00948   0.00404  -0.1524   0.4450   0.6148
   5.750   1.2696   0.00966   0.00421  -0.1518   0.4347   0.6175
   6.000   1.2916   0.00987   0.00440  -0.1507   0.4232   0.6201
   6.250   1.3136   0.01007   0.00458  -0.1498   0.4116   0.6227
   6.500   1.3353   0.01029   0.00478  -0.1487   0.3999   0.6250
   6.750   1.3562   0.01053   0.00501  -0.1475   0.3870   0.6281
   7.000   1.3764   0.01081   0.00527  -0.1463   0.3732   0.6312
   7.250   1.3959   0.01114   0.00555  -0.1449   0.3570   0.6346
   7.500   1.4142   0.01153   0.00588  -0.1433   0.3389   0.6380
   7.750   1.4315   0.01195   0.00623  -0.1416   0.3208   0.6410
   8.000   1.4483   0.01240   0.00662  -0.1398   0.3017   0.6447
   8.250   1.4650   0.01287   0.00702  -0.1380   0.2822   0.6484
   8.500   1.4801   0.01339   0.00748  -0.1360   0.2631   0.6524
   8.750   1.4937   0.01400   0.00799  -0.1338   0.2436   0.6562
   9.000   1.5072   0.01461   0.00854  -0.1316   0.2230   0.6605
   9.250   1.5188   0.01531   0.00917  -0.1292   0.2030   0.6652
   9.500   1.5295   0.01608   0.00985  -0.1267   0.1840   0.6703
   9.750   1.5394   0.01689   0.01059  -0.1241   0.1645   0.6756
  10.000   1.5488   0.01775   0.01140  -0.1215   0.1478   0.6817
  10.250   1.5566   0.01872   0.01230  -0.1188   0.1312   0.6879
  10.500   1.5640   0.01975   0.01328  -0.1162   0.1154   0.6947
  10.750   1.5713   0.02082   0.01431  -0.1137   0.1017   0.7024
  11.000   1.5780   0.02197   0.01544  -0.1112   0.0891   0.7107
  11.250   1.5827   0.02330   0.01673  -0.1087   0.0755   0.7203
  11.500   1.5867   0.02473   0.01814  -0.1062   0.0633   0.7314
  11.750   1.5905   0.02626   0.01967  -0.1039   0.0527   0.7443
  12.000   1.5914   0.02806   0.02146  -0.1015   0.0413   0.7600
  12.250   1.5903   0.03012   0.02352  -0.0991   0.0310   0.7797
  12.500   1.5886   0.03233   0.02577  -0.0969   0.0211   0.8067
  12.750   1.5838   0.03483   0.02836  -0.0946   0.0123   0.8551
  13.000   1.5807   0.03681   0.03053  -0.0921   0.0094   1.0000
  13.250   1.5846   0.03892   0.03269  -0.0910   0.0082   1.0000
  13.500   1.5885   0.04110   0.03493  -0.0899   0.0076   1.0000
  13.750   1.5907   0.04353   0.03742  -0.0890   0.0070   1.0000
  14.000   1.5943   0.04588   0.03986  -0.0882   0.0067   1.0000
  14.250   1.5986   0.04825   0.04230  -0.0876   0.0065   1.0000
  14.500   1.6018   0.05079   0.04492  -0.0871   0.0063   1.0000
  14.750   1.6041   0.05350   0.04771  -0.0866   0.0061   1.0000
  15.000   1.6058   0.05636   0.05064  -0.0863   0.0059   1.0000
  15.250   1.6065   0.05942   0.05379  -0.0862   0.0058   1.0000
  15.500   1.6063   0.06266   0.05712  -0.0861   0.0056   1.0000
  15.750   1.6052   0.06611   0.06065  -0.0862   0.0055   1.0000
  16.000   1.6028   0.06981   0.06444  -0.0864   0.0054   1.0000
  16.250   1.5988   0.07383   0.06856  -0.0868   0.0053   1.0000
  16.500   1.5935   0.07815   0.07299  -0.0874   0.0051   1.0000
  16.750   1.5865   0.08283   0.07778  -0.0882   0.0051   1.0000
  17.000   1.5771   0.08796   0.08305  -0.0893   0.0050   1.0000
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