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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 500,000
Max Cl/Cd: 103.28 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e560-il-500000-n5.txt
Download as CSV file: xf-e560-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.6144   0.14640   0.14335  -0.0373   1.0000   0.0128
 -18.000  -0.6317   0.13872   0.13555  -0.0409   1.0000   0.0129
 -17.750  -0.6430   0.13258   0.12933  -0.0438   1.0000   0.0129
 -17.500  -0.6501   0.12741   0.12409  -0.0461   1.0000   0.0130
 -17.250  -0.6578   0.12224   0.11885  -0.0485   1.0000   0.0131
 -17.000  -0.6632   0.11765   0.11419  -0.0505   1.0000   0.0132
 -16.750  -0.6678   0.11330   0.10978  -0.0523   1.0000   0.0131
 -16.500  -0.6724   0.10902   0.10545  -0.0542   1.0000   0.0133
 -16.250  -0.6766   0.10488   0.10125  -0.0559   1.0000   0.0133
 -16.000  -0.6804   0.10093   0.09725  -0.0575   1.0000   0.0134
 -15.750  -0.6849   0.09688   0.09315  -0.0591   1.0000   0.0136
 -15.500  -0.6881   0.09318   0.08940  -0.0605   1.0000   0.0136
 -15.250  -0.6912   0.08960   0.08578  -0.0618   1.0000   0.0137
 -15.000  -0.6958   0.08581   0.08194  -0.0632   1.0000   0.0137
 -14.750  -0.6998   0.08225   0.07833  -0.0644   1.0000   0.0138
 -14.500  -0.7050   0.07858   0.07461  -0.0657   1.0000   0.0139
 -14.250  -0.7103   0.07503   0.07101  -0.0668   1.0000   0.0140
 -14.000  -0.7168   0.07143   0.06736  -0.0679   1.0000   0.0141
 -13.750  -0.7234   0.06798   0.06387  -0.0689   1.0000   0.0141
 -13.500  -0.7320   0.06450   0.06035  -0.0697   1.0000   0.0141
 -13.250  -0.7340   0.06053   0.05632  -0.0727   0.9991   0.0142
 -13.000  -0.7300   0.05620   0.05191  -0.0776   0.9969   0.0143
 -12.750  -0.7264   0.05174   0.04737  -0.0831   0.9943   0.0143
 -12.500  -0.7286   0.04686   0.04241  -0.0885   0.9906   0.0145
 -12.250  -0.7298   0.04180   0.03727  -0.0946   0.9858   0.0147
 -12.000  -0.7334   0.03717   0.03255  -0.0996   0.9789   0.0147
 -11.500  -0.7133   0.02654   0.02161  -0.1163   0.9625   0.0151
 -11.250  -0.6920   0.02379   0.01871  -0.1210   0.9552   0.0154
 -11.000  -0.6658   0.02216   0.01697  -0.1238   0.9497   0.0157
 -10.750  -0.6410   0.02088   0.01560  -0.1254   0.9433   0.0161
 -10.500  -0.6144   0.01977   0.01441  -0.1268   0.9370   0.0166
 -10.250  -0.5829   0.01877   0.01331  -0.1288   0.9330   0.0171
 -10.000  -0.5567   0.01795   0.01240  -0.1295   0.9247   0.0175
  -9.750  -0.5225   0.01692   0.01128  -0.1320   0.9201   0.0181
  -9.500  -0.4896   0.01608   0.01038  -0.1338   0.9132   0.0189
  -9.250  -0.4514   0.01533   0.00954  -0.1366   0.9070   0.0198
  -9.000  -0.4094   0.01464   0.00877  -0.1400   0.9006   0.0211
  -8.750  -0.3652   0.01391   0.00798  -0.1440   0.8921   0.0236
  -8.500  -0.3159   0.01322   0.00724  -0.1491   0.8829   0.0295
  -8.250  -0.2711   0.01250   0.00651  -0.1533   0.8697   0.0439
  -8.000  -0.2334   0.01199   0.00597  -0.1558   0.8534   0.0572
  -7.750  -0.2007   0.01161   0.00553  -0.1571   0.8352   0.0689
  -7.500  -0.1711   0.01131   0.00518  -0.1577   0.8171   0.0797
  -7.250  -0.1430   0.01107   0.00487  -0.1579   0.7998   0.0904
  -7.000  -0.1158   0.01086   0.00460  -0.1579   0.7830   0.1019
  -6.750  -0.0889   0.01066   0.00435  -0.1578   0.7674   0.1140
  -6.500  -0.0621   0.01049   0.00413  -0.1577   0.7523   0.1251
  -6.250  -0.0354   0.01033   0.00393  -0.1575   0.7380   0.1375
  -6.000  -0.0085   0.01020   0.00375  -0.1573   0.7238   0.1489
  -5.750   0.0185   0.01012   0.00361  -0.1571   0.7108   0.1579
  -5.500   0.0456   0.01002   0.00347  -0.1569   0.6985   0.1682
  -5.250   0.0725   0.00995   0.00334  -0.1567   0.6861   0.1794
  -5.000   0.0998   0.00990   0.00323  -0.1565   0.6735   0.1888
  -4.750   0.1271   0.00983   0.00314  -0.1564   0.6623   0.1990
  -4.500   0.1543   0.00981   0.00305  -0.1561   0.6513   0.2064
  -4.250   0.1817   0.00978   0.00297  -0.1560   0.6399   0.2141
  -4.000   0.2091   0.00977   0.00289  -0.1557   0.6290   0.2205
  -3.750   0.2363   0.00976   0.00283  -0.1555   0.6189   0.2279
  -3.500   0.2641   0.00975   0.00277  -0.1554   0.6087   0.2342
  -3.250   0.2914   0.00975   0.00273  -0.1552   0.5987   0.2409
  -3.000   0.3188   0.00976   0.00269  -0.1550   0.5885   0.2479
  -2.750   0.3465   0.00977   0.00265  -0.1548   0.5795   0.2539
  -2.500   0.3738   0.00979   0.00263  -0.1546   0.5702   0.2610
  -2.250   0.4015   0.00982   0.00261  -0.1545   0.5613   0.2672
  -1.750   0.4564   0.00987   0.00260  -0.1541   0.5436   0.2807
  -1.250   0.5113   0.00995   0.00262  -0.1538   0.5274   0.2936
  -1.000   0.5383   0.01002   0.00264  -0.1535   0.5191   0.3000
  -0.750   0.5660   0.01005   0.00266  -0.1534   0.5114   0.3061
  -0.500   0.5932   0.01011   0.00270  -0.1531   0.5040   0.3132
  -0.250   0.6206   0.01017   0.00273  -0.1529   0.4971   0.3196
   0.000   0.6478   0.01023   0.00278  -0.1527   0.4895   0.3262
   0.250   0.6747   0.01031   0.00283  -0.1524   0.4825   0.3330
   0.500   0.7022   0.01037   0.00289  -0.1523   0.4759   0.3401
   0.750   0.7288   0.01046   0.00296  -0.1520   0.4695   0.3471
   1.000   0.7561   0.01053   0.00303  -0.1518   0.4633   0.3535
   1.250   0.7830   0.01061   0.00311  -0.1515   0.4565   0.3614
   1.500   0.8095   0.01072   0.00320  -0.1511   0.4506   0.3685
   1.750   0.8367   0.01078   0.00329  -0.1510   0.4450   0.3754
   2.000   0.8632   0.01089   0.00339  -0.1506   0.4390   0.3835
   2.250   0.8896   0.01099   0.00350  -0.1503   0.4334   0.3913
   2.500   0.9164   0.01108   0.00360  -0.1500   0.4276   0.3995
   2.750   0.9425   0.01119   0.00372  -0.1496   0.4223   0.4072
   3.000   0.9686   0.01131   0.00385  -0.1492   0.4174   0.4168
   3.250   0.9952   0.01140   0.00398  -0.1489   0.4120   0.4258
   3.500   1.0209   0.01153   0.00412  -0.1485   0.4066   0.4355
   3.750   1.0464   0.01167   0.00427  -0.1480   0.4019   0.4457
   4.000   1.0727   0.01176   0.00442  -0.1477   0.3972   0.4576
   4.250   1.0983   0.01189   0.00459  -0.1472   0.3920   0.4702
   4.500   1.1229   0.01205   0.00476  -0.1466   0.3871   0.4831
   4.750   1.1487   0.01216   0.00494  -0.1462   0.3827   0.4987
   5.000   1.1740   0.01228   0.00513  -0.1457   0.3777   0.5162
   5.250   1.1983   0.01244   0.00533  -0.1450   0.3728   0.5353
   5.500   1.2224   0.01259   0.00554  -0.1443   0.3685   0.5581
   5.750   1.2470   0.01269   0.00575  -0.1437   0.3637   0.5845
   6.000   1.2703   0.01283   0.00598  -0.1428   0.3586   0.6147
   6.250   1.2924   0.01300   0.00623  -0.1418   0.3539   0.6525
   6.500   1.3164   0.01309   0.00648  -0.1410   0.3491   0.6999
   6.750   1.3382   0.01319   0.00675  -0.1399   0.3439   0.7604
   7.000   1.3535   0.01325   0.00703  -0.1373   0.3389   0.8580
   7.250   1.3715   0.01328   0.00718  -0.1352   0.3344   1.0000
   7.500   1.3939   0.01352   0.00744  -0.1343   0.3287   1.0000
   7.750   1.4143   0.01384   0.00773  -0.1330   0.3230   1.0000
   8.000   1.4364   0.01408   0.00800  -0.1320   0.3174   1.0000
   8.250   1.4569   0.01439   0.00832  -0.1308   0.3108   1.0000
   8.500   1.4764   0.01474   0.00865  -0.1294   0.3048   1.0000
   8.750   1.4973   0.01503   0.00897  -0.1282   0.2984   1.0000
   9.000   1.5153   0.01544   0.00936  -0.1266   0.2917   1.0000
   9.250   1.5350   0.01578   0.00974  -0.1254   0.2852   1.0000
   9.500   1.5523   0.01622   0.01017  -0.1237   0.2776   1.0000
   9.750   1.5700   0.01665   0.01061  -0.1222   0.2699   1.0000
  10.000   1.5844   0.01722   0.01116  -0.1202   0.2605   1.0000
  10.250   1.6003   0.01775   0.01169  -0.1184   0.2503   1.0000
  10.500   1.6137   0.01840   0.01232  -0.1164   0.2404   1.0000
  10.750   1.6241   0.01920   0.01308  -0.1140   0.2269   1.0000
  11.000   1.6337   0.02009   0.01393  -0.1116   0.2143   1.0000
  11.250   1.6411   0.02112   0.01491  -0.1091   0.2002   1.0000
  11.500   1.6468   0.02230   0.01604  -0.1065   0.1858   1.0000
  11.750   1.6525   0.02353   0.01724  -0.1040   0.1733   1.0000
  12.000   1.6560   0.02497   0.01864  -0.1015   0.1602   1.0000
  12.250   1.6588   0.02652   0.02018  -0.0991   0.1483   1.0000
  12.500   1.6608   0.02823   0.02187  -0.0969   0.1375   1.0000
  12.750   1.6617   0.03011   0.02373  -0.0948   0.1276   1.0000
  13.000   1.6610   0.03222   0.02584  -0.0928   0.1179   1.0000
  13.250   1.6614   0.03438   0.02801  -0.0912   0.1091   1.0000
  13.500   1.6607   0.03673   0.03039  -0.0897   0.1018   1.0000
  13.750   1.6578   0.03942   0.03308  -0.0884   0.0938   1.0000
  14.000   1.6559   0.04215   0.03584  -0.0873   0.0868   1.0000
  14.250   1.6511   0.04530   0.03901  -0.0864   0.0805   1.0000
  14.500   1.6474   0.04846   0.04222  -0.0858   0.0738   1.0000
  14.750   1.6419   0.05196   0.04575  -0.0853   0.0684   1.0000
  15.000   1.6370   0.05553   0.04937  -0.0851   0.0630   1.0000
  15.250   1.6312   0.05933   0.05322  -0.0851   0.0589   1.0000
  15.500   1.6261   0.06315   0.05711  -0.0852   0.0547   1.0000
  15.750   1.6190   0.06736   0.06137  -0.0856   0.0510   1.0000
  16.000   1.6141   0.07139   0.06548  -0.0861   0.0476   1.0000
  16.250   1.6068   0.07584   0.06999  -0.0867   0.0445   1.0000
  16.500   1.6012   0.08016   0.07438  -0.0875   0.0419   1.0000
  16.750   1.5947   0.08468   0.07897  -0.0885   0.0388   1.0000
  17.000   1.5872   0.08945   0.08381  -0.0896   0.0366   1.0000
  17.250   1.5820   0.09392   0.08836  -0.0908   0.0343   1.0000
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