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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.1 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e560-il-1000000.txt
Download as CSV file: xf-e560-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 560 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
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.6583   0.14189   0.13961  -0.0382   1.0000   0.0133
 -18.250  -0.6804   0.13343   0.13103  -0.0425   1.0000   0.0133
 -18.000  -0.6969   0.12637   0.12387  -0.0460   1.0000   0.0134
 -17.750  -0.7075   0.12070   0.11812  -0.0487   1.0000   0.0134
 -17.500  -0.7156   0.11565   0.11300  -0.0511   1.0000   0.0134
 -17.250  -0.7241   0.11057   0.10785  -0.0535   1.0000   0.0135
 -17.000  -0.7301   0.10610   0.10332  -0.0555   1.0000   0.0136
 -16.750  -0.7356   0.10182   0.09897  -0.0574   1.0000   0.0135
 -16.500  -0.7414   0.09753   0.09463  -0.0592   1.0000   0.0137
 -16.250  -0.7465   0.09344   0.09049  -0.0610   1.0000   0.0137
 -16.000  -0.7510   0.08964   0.08663  -0.0625   1.0000   0.0137
 -15.750  -0.7568   0.08552   0.08245  -0.0643   1.0000   0.0139
 -15.500  -0.7607   0.08189   0.07877  -0.0657   1.0000   0.0139
 -15.250  -0.7646   0.07839   0.07522  -0.0669   1.0000   0.0139
 -15.000  -0.7700   0.07457   0.07135  -0.0685   1.0000   0.0141
 -14.750  -0.7754   0.07101   0.06774  -0.0697   1.0000   0.0141
 -14.500  -0.7805   0.06772   0.06440  -0.0706   1.0000   0.0141
 -14.250  -0.7874   0.06415   0.06077  -0.0718   1.0000   0.0142
 -14.000  -0.7943   0.06094   0.05752  -0.0725   1.0000   0.0142
 -13.750  -0.8036   0.05772   0.05425  -0.0731   1.0000   0.0143
 -13.500  -0.8153   0.05452   0.05101  -0.0733   1.0000   0.0143
 -13.250  -0.8157   0.05089   0.04732  -0.0765   0.9989   0.0143
 -13.000  -0.8132   0.04620   0.04254  -0.0828   0.9960   0.0144
 -12.750  -0.8068   0.04151   0.03776  -0.0899   0.9934   0.0145
 -12.500  -0.8133   0.03612   0.03227  -0.0963   0.9865   0.0147
 -12.250  -0.7940   0.02997   0.02599  -0.1084   0.9834   0.0150
 -12.000  -0.7744   0.02434   0.02018  -0.1190   0.9762   0.0151
 -11.750  -0.7419   0.02199   0.01771  -0.1248   0.9739   0.0154
 -11.500  -0.7074   0.02040   0.01603  -0.1291   0.9726   0.0157
 -11.250  -0.6853   0.01920   0.01475  -0.1298   0.9671   0.0160
 -11.000  -0.6543   0.01813   0.01361  -0.1320   0.9640   0.0163
 -10.750  -0.6205   0.01716   0.01257  -0.1345   0.9621   0.0167
 -10.500  -0.5852   0.01630   0.01164  -0.1370   0.9606   0.0171
 -10.250  -0.5631   0.01560   0.01089  -0.1365   0.9537   0.0173
 -10.000  -0.5308   0.01489   0.01012  -0.1380   0.9504   0.0176
  -9.750  -0.4973   0.01385   0.00900  -0.1401   0.9480   0.0184
  -9.500  -0.4735   0.01320   0.00831  -0.1398   0.9400   0.0191
  -9.250  -0.4402   0.01258   0.00765  -0.1412   0.9359   0.0199
  -9.000  -0.4050   0.01204   0.00705  -0.1430   0.9311   0.0208
  -8.750  -0.3688   0.01146   0.00642  -0.1450   0.9242   0.0221
  -8.500  -0.3235   0.01085   0.00578  -0.1489   0.9193   0.0247
  -8.250  -0.2787   0.01011   0.00508  -0.1530   0.9105   0.0375
  -8.000  -0.2269   0.00934   0.00443  -0.1587   0.9008   0.0646
  -7.750  -0.1853   0.00894   0.00403  -0.1618   0.8847   0.0810
  -7.500  -0.1517   0.00868   0.00374  -0.1632   0.8650   0.0946
  -7.250  -0.1223   0.00850   0.00351  -0.1635   0.8450   0.1066
  -7.000  -0.0949   0.00836   0.00330  -0.1635   0.8257   0.1187
  -6.750  -0.0682   0.00825   0.00314  -0.1632   0.8078   0.1295
  -6.500  -0.0417   0.00813   0.00299  -0.1629   0.7910   0.1414
  -6.250  -0.0153   0.00804   0.00285  -0.1625   0.7746   0.1514
  -6.000   0.0114   0.00798   0.00273  -0.1622   0.7592   0.1602
  -5.750   0.0383   0.00792   0.00262  -0.1619   0.7448   0.1703
  -5.500   0.0652   0.00786   0.00252  -0.1616   0.7308   0.1795
  -5.250   0.0921   0.00785   0.00244  -0.1613   0.7172   0.1875
  -4.750   0.1467   0.00778   0.00229  -0.1609   0.6915   0.2046
  -4.500   0.1741   0.00775   0.00223  -0.1607   0.6794   0.2139
  -4.250   0.2014   0.00775   0.00218  -0.1604   0.6672   0.2223
  -4.000   0.2289   0.00774   0.00214  -0.1603   0.6552   0.2306
  -3.750   0.2568   0.00775   0.00210  -0.1601   0.6445   0.2370
  -3.500   0.2842   0.00774   0.00206  -0.1599   0.6335   0.2442
  -3.250   0.3119   0.00778   0.00203  -0.1597   0.6222   0.2504
  -3.000   0.3398   0.00777   0.00200  -0.1596   0.6118   0.2572
  -2.750   0.3672   0.00780   0.00199  -0.1594   0.6015   0.2638
  -2.500   0.3953   0.00782   0.00197  -0.1593   0.5917   0.2699
  -2.250   0.4230   0.00784   0.00196  -0.1592   0.5820   0.2769
  -2.000   0.4506   0.00789   0.00196  -0.1590   0.5718   0.2831
  -1.750   0.4786   0.00790   0.00196  -0.1589   0.5630   0.2900
  -1.500   0.5061   0.00795   0.00198  -0.1587   0.5538   0.2969
  -1.250   0.5341   0.00799   0.00199  -0.1586   0.5453   0.3031
  -0.750   0.5895   0.00808   0.00203  -0.1583   0.5278   0.3165
  -0.500   0.6168   0.00814   0.00207  -0.1581   0.5194   0.3236
  -0.250   0.6449   0.00818   0.00210  -0.1580   0.5120   0.3304
   0.000   0.6721   0.00826   0.00214  -0.1578   0.5037   0.3366
   0.250   0.7000   0.00830   0.00219  -0.1577   0.4964   0.3444
   0.500   0.7273   0.00839   0.00224  -0.1575   0.4888   0.3509
   0.750   0.7548   0.00844   0.00229  -0.1573   0.4821   0.3582
   1.000   0.7823   0.00851   0.00235  -0.1572   0.4751   0.3658
   1.250   0.8091   0.00861   0.00242  -0.1569   0.4678   0.3729
   1.500   0.8370   0.00865   0.00249  -0.1568   0.4617   0.3807
   1.750   0.8639   0.00875   0.00257  -0.1565   0.4552   0.3879
   2.000   0.8910   0.00882   0.00265  -0.1563   0.4493   0.3968
   2.250   0.9183   0.00890   0.00273  -0.1561   0.4432   0.4043
   2.500   0.9447   0.00901   0.00283  -0.1557   0.4366   0.4134
   2.750   0.9720   0.00908   0.00292  -0.1555   0.4315   0.4226
   3.000   0.9990   0.00915   0.00302  -0.1553   0.4259   0.4329
   3.250   1.0249   0.00928   0.00314  -0.1549   0.4198   0.4426
   3.500   1.0521   0.00935   0.00324  -0.1547   0.4150   0.4544
   3.750   1.0788   0.00943   0.00336  -0.1544   0.4098   0.4674
   4.000   1.1045   0.00956   0.00350  -0.1540   0.4041   0.4811
   4.250   1.1312   0.00964   0.00362  -0.1537   0.3994   0.4964
   4.500   1.1577   0.00972   0.00375  -0.1534   0.3945   0.5150
   4.750   1.1831   0.00985   0.00391  -0.1529   0.3891   0.5362
   5.250   1.2353   0.01002   0.00422  -0.1522   0.3796   0.5889
   5.500   1.2606   0.01013   0.00441  -0.1517   0.3743   0.6245
   5.750   1.2854   0.01024   0.00461  -0.1512   0.3692   0.6671
   6.000   1.3113   0.01027   0.00479  -0.1508   0.3647   0.7200
   6.250   1.3349   0.01031   0.00500  -0.1499   0.3596   0.7933
   6.500   1.3471   0.01019   0.00517  -0.1465   0.3544   1.0000
   6.750   1.3723   0.01031   0.00531  -0.1460   0.3501   1.0000
   7.000   1.3961   0.01049   0.00548  -0.1452   0.3447   1.0000
   7.250   1.4179   0.01075   0.00570  -0.1440   0.3387   1.0000
   7.500   1.4421   0.01090   0.00588  -0.1434   0.3340   1.0000
   7.750   1.4650   0.01110   0.00607  -0.1424   0.3286   1.0000
   8.000   1.4857   0.01139   0.00633  -0.1411   0.3224   1.0000
   8.250   1.5096   0.01155   0.00652  -0.1404   0.3177   1.0000
   8.500   1.5314   0.01179   0.00676  -0.1393   0.3114   1.0000
   8.750   1.5522   0.01208   0.00702  -0.1381   0.3046   1.0000
   9.000   1.5734   0.01233   0.00728  -0.1370   0.2966   1.0000
   9.250   1.5928   0.01266   0.00758  -0.1355   0.2885   1.0000
   9.500   1.6126   0.01299   0.00788  -0.1342   0.2797   1.0000
   9.750   1.6316   0.01334   0.00822  -0.1327   0.2704   1.0000
  10.000   1.6481   0.01380   0.00864  -0.1309   0.2602   1.0000
  10.250   1.6661   0.01419   0.00901  -0.1293   0.2503   1.0000
  10.500   1.6824   0.01467   0.00946  -0.1275   0.2403   1.0000
  10.750   1.6965   0.01524   0.00999  -0.1254   0.2292   1.0000
  11.000   1.7097   0.01586   0.01057  -0.1231   0.2168   1.0000
  11.250   1.7221   0.01653   0.01120  -0.1209   0.2044   1.0000
  11.500   1.7315   0.01735   0.01196  -0.1183   0.1903   1.0000
  11.750   1.7378   0.01836   0.01288  -0.1153   0.1748   1.0000
  12.000   1.7443   0.01938   0.01385  -0.1125   0.1616   1.0000
  12.250   1.7504   0.02047   0.01490  -0.1098   0.1498   1.0000
  12.500   1.7542   0.02173   0.01612  -0.1070   0.1377   1.0000
  12.750   1.7567   0.02315   0.01749  -0.1042   0.1261   1.0000
  13.000   1.7578   0.02473   0.01904  -0.1015   0.1152   1.0000
  13.250   1.7582   0.02646   0.02074  -0.0989   0.1054   1.0000
  13.500   1.7609   0.02812   0.02240  -0.0968   0.0975   1.0000
  13.750   1.7609   0.03009   0.02436  -0.0947   0.0899   1.0000
  14.000   1.7604   0.03221   0.02649  -0.0929   0.0829   1.0000
  14.250   1.7609   0.03437   0.02867  -0.0913   0.0769   1.0000
  14.500   1.7575   0.03699   0.03130  -0.0897   0.0707   1.0000
  14.750   1.7577   0.03940   0.03375  -0.0886   0.0659   1.0000
  15.000   1.7525   0.04248   0.03684  -0.0875   0.0605   1.0000
  15.250   1.7508   0.04533   0.03974  -0.0867   0.0562   1.0000
  15.750   1.7411   0.05207   0.04656  -0.0856   0.0481   1.0000
  16.000   1.7334   0.05598   0.05051  -0.0855   0.0444   1.0000
  16.250   1.7282   0.05971   0.05430  -0.0855   0.0411   1.0000
  16.500   1.7202   0.06392   0.05856  -0.0857   0.0379   1.0000
  16.750   1.7129   0.06817   0.06287  -0.0861   0.0348   1.0000
  17.000   1.7042   0.07274   0.06750  -0.0867   0.0320   1.0000
  17.250   1.6949   0.07749   0.07232  -0.0875   0.0291   1.0000
  17.500   1.6836   0.08266   0.07754  -0.0886   0.0260   1.0000
  17.750   1.6744   0.08764   0.08258  -0.0898   0.0233   1.0000
  18.000   1.6619   0.09321   0.08820  -0.0912   0.0200   1.0000
  18.250   1.6491   0.09892   0.09397  -0.0929   0.0170   1.0000
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