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EPPLER 656 AIRFOIL (e656-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 656 AIRFOIL (e656-il)
Reynolds number: 500,000
Max Cl/Cd: 125.41 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e656-il-500000.txt
Download as CSV file: xf-e656-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 656 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.0240   0.10506   0.10163  -0.0989   0.7521   0.0207
 -12.000  -0.0367   0.09804   0.09462  -0.1028   0.7511   0.0219
 -11.750  -0.0384   0.09310   0.08968  -0.1048   0.7495   0.0221
 -11.500  -0.0293   0.09084   0.08739  -0.1052   0.7476   0.0223
 -11.250  -0.0220   0.08821   0.08473  -0.1060   0.7456   0.0225
 -11.000  -0.0160   0.08531   0.08184  -0.1070   0.7440   0.0229
 -10.750  -0.0130   0.08174   0.07829  -0.1083   0.7426   0.0232
 -10.500  -0.0117   0.07786   0.07442  -0.1097   0.7411   0.0238
 -10.250  -0.0136   0.07333   0.06991  -0.1115   0.7396   0.0244
 -10.000  -0.0524   0.07540   0.07177  -0.1233   0.7440   0.0235
  -8.500  -0.2697   0.02852   0.02319  -0.1270   0.7305   0.0127
  -8.250  -0.2599   0.02606   0.02050  -0.1255   0.7285   0.0122
  -8.000  -0.2479   0.02359   0.01768  -0.1240   0.7264   0.0116
  -7.750  -0.2338   0.02084   0.01441  -0.1222   0.7250   0.0108
  -7.500  -0.2124   0.01960   0.01297  -0.1215   0.7234   0.0107
  -7.250  -0.1902   0.01855   0.01180  -0.1209   0.7218   0.0107
  -7.000  -0.1672   0.01769   0.01085  -0.1204   0.7200   0.0108
  -6.750  -0.1439   0.01692   0.01000  -0.1199   0.7183   0.0110
  -6.500  -0.1202   0.01624   0.00927  -0.1195   0.7165   0.0112
  -6.250  -0.0959   0.01565   0.00861  -0.1191   0.7147   0.0116
  -6.000  -0.0714   0.01510   0.00799  -0.1188   0.7131   0.0122
  -5.750  -0.0461   0.01466   0.00747  -0.1185   0.7116   0.0127
  -5.500  -0.0217   0.01413   0.00691  -0.1183   0.7100   0.0140
  -5.250   0.0042   0.01383   0.00656  -0.1182   0.7085   0.0154
  -5.000   0.0297   0.01339   0.00612  -0.1180   0.7071   0.0181
  -4.750   0.0555   0.01297   0.00573  -0.1178   0.7055   0.0251
  -4.500   0.0813   0.01255   0.00541  -0.1178   0.7037   0.0411
  -4.250   0.1078   0.01224   0.00521  -0.1178   0.7020   0.0619
  -4.000   0.1345   0.01194   0.00504  -0.1180   0.7005   0.0912
  -3.750   0.1612   0.01161   0.00487  -0.1182   0.6989   0.1345
  -3.500   0.1884   0.01131   0.00481  -0.1185   0.6973   0.2009
  -3.250   0.2165   0.01116   0.00468  -0.1188   0.6958   0.2316
  -3.000   0.2444   0.01092   0.00453  -0.1191   0.6942   0.2603
  -2.750   0.2719   0.01063   0.00449  -0.1196   0.6927   0.3407
  -2.500   0.2992   0.01037   0.00451  -0.1200   0.6911   0.4303
  -2.250   0.3261   0.00997   0.00448  -0.1203   0.6898   0.5347
  -2.000   0.3529   0.00969   0.00452  -0.1204   0.6881   0.6294
  -1.750   0.3797   0.00962   0.00465  -0.1202   0.6862   0.6925
  -1.500   0.4071   0.00968   0.00478  -0.1200   0.6845   0.7289
  -1.250   0.4350   0.00977   0.00488  -0.1200   0.6827   0.7528
  -1.000   0.4631   0.00987   0.00497  -0.1200   0.6809   0.7705
  -0.750   0.4916   0.00997   0.00503  -0.1201   0.6792   0.7833
  -0.500   0.5205   0.01008   0.00510  -0.1204   0.6776   0.7950
  -0.250   0.5483   0.01022   0.00521  -0.1203   0.6759   0.8046
   0.000   0.5771   0.01046   0.00539  -0.1205   0.6739   0.8134
   0.250   0.6037   0.01049   0.00545  -0.1203   0.6720   0.8188
   0.500   0.6303   0.01056   0.00554  -0.1202   0.6698   0.8243
   0.750   0.6582   0.01062   0.00559  -0.1203   0.6674   0.8304
   1.000   0.6859   0.01066   0.00563  -0.1204   0.6651   0.8351
   1.250   0.7133   0.01070   0.00566  -0.1203   0.6629   0.8395
   1.500   0.7419   0.01074   0.00567  -0.1205   0.6608   0.8450
   1.750   0.7712   0.01080   0.00569  -0.1209   0.6588   0.8509
   2.000   0.7972   0.01095   0.00585  -0.1205   0.6564   0.8564
   2.250   0.8221   0.01099   0.00594  -0.1200   0.6537   0.8631
   2.500   0.8479   0.01101   0.00599  -0.1197   0.6507   0.8686
   2.750   0.8731   0.01100   0.00601  -0.1192   0.6477   0.8734
   3.000   0.9007   0.01098   0.00599  -0.1192   0.6449   0.8784
   3.250   0.9308   0.01098   0.00594  -0.1198   0.6423   0.8831
   3.500   0.9572   0.01103   0.00598  -0.1196   0.6394   0.8865
   3.750   0.9804   0.01101   0.00604  -0.1188   0.6360   0.8906
   4.000   1.0062   0.01099   0.00607  -0.1185   0.6323   0.8950
   4.500   1.0608   0.01088   0.00596  -0.1186   0.6258   0.9026
   4.750   1.0870   0.01089   0.00598  -0.1184   0.6223   0.9062
   5.000   1.1104   0.01086   0.00604  -0.1177   0.6177   0.9102
   5.250   1.1372   0.01082   0.00602  -0.1177   0.6130   0.9138
   5.500   1.1632   0.01072   0.00593  -0.1175   0.6088   0.9170
   5.750   1.1857   0.01070   0.00597  -0.1166   0.6037   0.9209
   6.000   1.2085   0.01067   0.00600  -0.1158   0.5977   0.9253
   6.250   1.2343   0.01062   0.00595  -0.1156   0.5923   0.9296
   6.500   1.2530   0.01060   0.00602  -0.1140   0.5856   0.9346
   6.750   1.2743   0.01057   0.00603  -0.1129   0.5783   0.9396
   7.000   1.2945   0.01059   0.00610  -0.1116   0.5704   0.9452
   7.250   1.3112   0.01058   0.00612  -0.1095   0.5613   0.9524
   7.500   1.3274   0.01063   0.00622  -0.1075   0.5507   0.9603
   7.750   1.3431   0.01071   0.00632  -0.1054   0.5383   0.9719
   8.000   1.3649   0.01089   0.00650  -0.1049   0.5231   1.0000
   8.250   1.3808   0.01125   0.00682  -0.1033   0.5057   1.0000
   8.500   1.3933   0.01175   0.00726  -0.1013   0.4858   1.0000
   8.750   1.4021   0.01242   0.00784  -0.0988   0.4656   1.0000
   9.000   1.4081   0.01323   0.00858  -0.0959   0.4452   1.0000
   9.250   1.4125   0.01418   0.00947  -0.0930   0.4254   1.0000
   9.500   1.4145   0.01532   0.01053  -0.0900   0.4058   1.0000
   9.750   1.4152   0.01662   0.01178  -0.0870   0.3867   1.0000
  10.000   1.4154   0.01807   0.01316  -0.0842   0.3683   1.0000
  10.250   1.4152   0.01963   0.01465  -0.0815   0.3502   1.0000
  10.500   1.4155   0.02126   0.01621  -0.0791   0.3328   1.0000
  10.750   1.4162   0.02292   0.01782  -0.0768   0.3158   1.0000
  11.000   1.4173   0.02462   0.01947  -0.0746   0.2992   1.0000
  11.250   1.4185   0.02637   0.02116  -0.0726   0.2822   1.0000
  11.750   1.4236   0.02983   0.02452  -0.0691   0.2515   1.0000
  12.000   1.4274   0.03155   0.02622  -0.0676   0.2372   1.0000
  12.250   1.4310   0.03334   0.02797  -0.0661   0.2224   1.0000
  12.500   1.4350   0.03516   0.02975  -0.0648   0.2083   1.0000
  12.750   1.4389   0.03702   0.03157  -0.0636   0.1944   1.0000
  13.000   1.4430   0.03892   0.03343  -0.0624   0.1814   1.0000
  13.250   1.4473   0.04085   0.03533  -0.0614   0.1693   1.0000
  13.500   1.4508   0.04290   0.03735  -0.0604   0.1579   1.0000
  13.750   1.4558   0.04486   0.03928  -0.0595   0.1468   1.0000
  14.000   1.4609   0.04687   0.04128  -0.0587   0.1362   1.0000
  14.250   1.4659   0.04891   0.04331  -0.0580   0.1264   1.0000
  14.500   1.4690   0.05119   0.04558  -0.0573   0.1171   1.0000
  14.750   1.4733   0.05339   0.04777  -0.0567   0.1081   1.0000
  15.000   1.4778   0.05564   0.05003  -0.0562   0.0995   1.0000
  15.250   1.4811   0.05805   0.05244  -0.0558   0.0917   1.0000
  15.500   1.4829   0.06069   0.05506  -0.0554   0.0839   1.0000
  15.750   1.4865   0.06315   0.05755  -0.0551   0.0770   1.0000
  16.000   1.4896   0.06574   0.06016  -0.0550   0.0706   1.0000
  16.250   1.4902   0.06868   0.06311  -0.0548   0.0649   1.0000
  16.500   1.4927   0.07146   0.06592  -0.0548   0.0595   1.0000
  16.750   1.4943   0.07437   0.06887  -0.0549   0.0545   1.0000
  17.000   1.4926   0.07777   0.07228  -0.0550   0.0503   1.0000
  17.250   1.4952   0.08069   0.07525  -0.0553   0.0459   1.0000
  17.500   1.4943   0.08413   0.07875  -0.0557   0.0424   1.0000
  17.750   1.4933   0.08763   0.08229  -0.0562   0.0392   1.0000
  18.000   1.4929   0.09109   0.08583  -0.0568   0.0361   1.0000
  18.250   1.4891   0.09510   0.08986  -0.0576   0.0334   1.0000
  18.500   1.4894   0.09858   0.09344  -0.0584   0.0310   1.0000
  18.750   1.4851   0.10279   0.09770  -0.0595   0.0291   1.0000
  19.000   1.4844   0.10649   0.10148  -0.0606   0.0269   1.0000
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