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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 200,000
Max Cl/Cd: 74.81 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e562-il-200000-n5.txt
Download as CSV file: xf-e562-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 562 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.5779   0.10895   0.10473  -0.0488   1.0000   0.0158
 -14.500  -0.6078   0.09885   0.09448  -0.0539   1.0000   0.0156
 -14.250  -0.6328   0.09027   0.08574  -0.0585   1.0000   0.0156
 -14.000  -0.6527   0.08313   0.07844  -0.0623   1.0000   0.0158
 -13.750  -0.6673   0.07738   0.07256  -0.0652   1.0000   0.0158
 -13.500  -0.6803   0.07226   0.06732  -0.0676   1.0000   0.0158
 -13.250  -0.6962   0.06703   0.06191  -0.0702   1.0000   0.0162
 -13.000  -0.7057   0.06308   0.05786  -0.0716   1.0000   0.0162
 -12.750  -0.7152   0.05931   0.05397  -0.0727   1.0000   0.0163
 -12.500  -0.7233   0.05599   0.05063  -0.0736   1.0000   0.0167
 -12.250  -0.7299   0.05304   0.04762  -0.0738   1.0000   0.0168
 -12.000  -0.7368   0.05023   0.04477  -0.0740   1.0000   0.0170
 -11.750  -0.7450   0.04751   0.04201  -0.0738   1.0000   0.0172
 -11.500  -0.7541   0.04497   0.03943  -0.0733   1.0000   0.0174
 -11.250  -0.7660   0.04256   0.03698  -0.0721   1.0000   0.0175
 -11.000  -0.7831   0.04036   0.03474  -0.0701   1.0000   0.0176
 -10.750  -0.7954   0.03800   0.03231  -0.0694   0.9995   0.0178
 -10.500  -0.7694   0.03500   0.02913  -0.0758   0.9946   0.0185
 -10.250  -0.7437   0.03260   0.02654  -0.0802   0.9896   0.0193
 -10.000  -0.7152   0.03064   0.02437  -0.0839   0.9852   0.0201
  -9.750  -0.6897   0.02868   0.02236  -0.0869   0.9800   0.0209
  -9.500  -0.6610   0.02715   0.02076  -0.0897   0.9750   0.0221
  -9.250  -0.6311   0.02583   0.01929  -0.0921   0.9706   0.0237
  -9.000  -0.6045   0.02447   0.01783  -0.0938   0.9643   0.0251
  -8.750  -0.5715   0.02320   0.01649  -0.0966   0.9607   0.0269
  -8.500  -0.5462   0.02215   0.01534  -0.0974   0.9532   0.0287
  -8.250  -0.5130   0.02102   0.01412  -0.0998   0.9490   0.0313
  -8.000  -0.4853   0.02013   0.01316  -0.1007   0.9420   0.0343
  -7.750  -0.4526   0.01916   0.01213  -0.1026   0.9370   0.0383
  -7.500  -0.4198   0.01829   0.01119  -0.1043   0.9320   0.0444
  -7.250  -0.3903   0.01743   0.01032  -0.1053   0.9248   0.0535
  -6.750  -0.3263   0.01577   0.00876  -0.1082   0.9127   0.0926
  -6.500  -0.2917   0.01506   0.00809  -0.1100   0.9071   0.1169
  -6.250  -0.2582   0.01445   0.00754  -0.1115   0.9004   0.1435
  -6.000  -0.2238   0.01394   0.00708  -0.1131   0.8931   0.1710
  -5.750  -0.1858   0.01349   0.00666  -0.1153   0.8869   0.2004
  -5.500  -0.1502   0.01315   0.00635  -0.1170   0.8782   0.2284
  -5.250  -0.1093   0.01286   0.00603  -0.1196   0.8709   0.2490
  -5.000  -0.0694   0.01263   0.00574  -0.1221   0.8612   0.2647
  -4.750  -0.0292   0.01244   0.00548  -0.1245   0.8510   0.2801
  -4.500   0.0125   0.01226   0.00519  -0.1273   0.8401   0.2932
  -4.250   0.0499   0.01212   0.00498  -0.1291   0.8269   0.3043
  -4.000   0.0851   0.01201   0.00479  -0.1305   0.8128   0.3142
  -3.750   0.1188   0.01195   0.00460  -0.1315   0.7982   0.3252
  -3.500   0.1507   0.01190   0.00449  -0.1323   0.7835   0.3361
  -3.250   0.1814   0.01188   0.00438  -0.1327   0.7688   0.3466
  -3.000   0.2112   0.01188   0.00426  -0.1330   0.7544   0.3559
  -2.750   0.2402   0.01187   0.00418  -0.1330   0.7401   0.3635
  -2.500   0.2688   0.01189   0.00408  -0.1331   0.7261   0.3727
  -2.250   0.2966   0.01190   0.00404  -0.1329   0.7123   0.3803
  -2.000   0.3242   0.01193   0.00397  -0.1327   0.6985   0.3886
  -1.750   0.3514   0.01196   0.00395  -0.1325   0.6854   0.3964
  -1.500   0.3788   0.01201   0.00391  -0.1323   0.6727   0.4053
  -1.250   0.4059   0.01205   0.00391  -0.1320   0.6602   0.4128
  -1.000   0.4329   0.01212   0.00389  -0.1317   0.6479   0.4217
  -0.750   0.4596   0.01217   0.00391  -0.1314   0.6358   0.4294
  -0.500   0.4865   0.01224   0.00391  -0.1311   0.6242   0.4383
  -0.250   0.5131   0.01231   0.00395  -0.1307   0.6131   0.4462
   0.000   0.5398   0.01239   0.00398  -0.1304   0.6016   0.4552
   0.250   0.5663   0.01246   0.00404  -0.1301   0.5908   0.4631
   0.500   0.5929   0.01256   0.00408  -0.1297   0.5806   0.4725
   0.750   0.6192   0.01263   0.00416  -0.1293   0.5699   0.4805
   1.250   0.6719   0.01283   0.00432  -0.1286   0.5502   0.4987
   1.500   0.6983   0.01293   0.00441  -0.1283   0.5404   0.5082
   1.750   0.7243   0.01305   0.00452  -0.1278   0.5314   0.5179
   2.000   0.7504   0.01315   0.00464  -0.1274   0.5219   0.5279
   2.250   0.7765   0.01328   0.00476  -0.1270   0.5132   0.5388
   2.500   0.8023   0.01339   0.00491  -0.1266   0.5041   0.5497
   2.750   0.8281   0.01352   0.00506  -0.1262   0.4956   0.5613
   3.000   0.8537   0.01365   0.00523  -0.1257   0.4870   0.5741
   3.250   0.8793   0.01378   0.00540  -0.1252   0.4787   0.5878
   3.500   0.9043   0.01393   0.00558  -0.1246   0.4705   0.6024
   3.750   0.9296   0.01406   0.00579  -0.1241   0.4626   0.6188
   4.000   0.9543   0.01422   0.00599  -0.1234   0.4546   0.6367
   4.250   0.9792   0.01436   0.00621  -0.1228   0.4470   0.6569
   4.500   1.0033   0.01451   0.00645  -0.1221   0.4392   0.6799
   4.750   1.0272   0.01465   0.00669  -0.1212   0.4320   0.7067
   5.000   1.0501   0.01479   0.00694  -0.1202   0.4245   0.7388
   5.250   1.0719   0.01492   0.00718  -0.1189   0.4176   0.7787
   5.500   1.0911   0.01499   0.00741  -0.1170   0.4103   0.8340
   5.750   1.1091   0.01497   0.00751  -0.1147   0.4038   1.0000
   6.000   1.1340   0.01522   0.00779  -0.1142   0.3958   1.0000
   6.250   1.1578   0.01554   0.00808  -0.1136   0.3888   1.0000
   6.500   1.1820   0.01580   0.00839  -0.1130   0.3809   1.0000
   6.750   1.2048   0.01613   0.00869  -0.1122   0.3734   1.0000
   7.000   1.2280   0.01642   0.00902  -0.1114   0.3653   1.0000
   7.250   1.2496   0.01677   0.00936  -0.1104   0.3574   1.0000
   7.500   1.2717   0.01707   0.00972  -0.1094   0.3488   1.0000
   7.750   1.2917   0.01745   0.01008  -0.1081   0.3407   1.0000
   8.000   1.3119   0.01777   0.01047  -0.1068   0.3317   1.0000
   8.250   1.3303   0.01816   0.01087  -0.1052   0.3234   1.0000
   8.500   1.3484   0.01855   0.01129  -0.1036   0.3138   1.0000
   8.750   1.3659   0.01897   0.01175  -0.1019   0.3045   1.0000
   9.000   1.3815   0.01946   0.01224  -0.1000   0.2949   1.0000
   9.250   1.3983   0.01992   0.01275  -0.0983   0.2844   1.0000
   9.500   1.4135   0.02045   0.01331  -0.0963   0.2744   1.0000
   9.750   1.4264   0.02107   0.01393  -0.0941   0.2638   1.0000
  10.000   1.4406   0.02167   0.01458  -0.0922   0.2524   1.0000
  10.250   1.4531   0.02236   0.01530  -0.0901   0.2411   1.0000
  10.500   1.4638   0.02315   0.01611  -0.0878   0.2296   1.0000
  10.750   1.4728   0.02405   0.01701  -0.0854   0.2175   1.0000
  11.000   1.4803   0.02507   0.01803  -0.0829   0.2047   1.0000
  11.250   1.4872   0.02619   0.01915  -0.0806   0.1913   1.0000
  11.500   1.4927   0.02745   0.02042  -0.0783   0.1780   1.0000
  11.750   1.4967   0.02888   0.02186  -0.0760   0.1648   1.0000
  12.000   1.4993   0.03049   0.02346  -0.0738   0.1521   1.0000
  12.250   1.5006   0.03229   0.02527  -0.0718   0.1400   1.0000
  12.500   1.5009   0.03428   0.02726  -0.0699   0.1292   1.0000
  12.750   1.4996   0.03652   0.02951  -0.0683   0.1191   1.0000
  13.000   1.4992   0.03882   0.03185  -0.0669   0.1099   1.0000
  13.250   1.4979   0.04131   0.03439  -0.0657   0.1016   1.0000
  13.500   1.4940   0.04421   0.03731  -0.0648   0.0944   1.0000
  13.750   1.4929   0.04696   0.04014  -0.0641   0.0873   1.0000
  14.000   1.4881   0.05022   0.04346  -0.0637   0.0813   1.0000
  14.250   1.4853   0.05341   0.04673  -0.0634   0.0754   1.0000
  14.500   1.4791   0.05713   0.05051  -0.0635   0.0707   1.0000
  14.750   1.4759   0.06061   0.05408  -0.0636   0.0658   1.0000
  15.000   1.4689   0.06470   0.05824  -0.0641   0.0615   1.0000
  15.250   1.4640   0.06868   0.06231  -0.0647   0.0577   1.0000
  15.500   1.4579   0.07289   0.06662  -0.0655   0.0539   1.0000
  15.750   1.4489   0.07769   0.07148  -0.0666   0.0509   1.0000
  16.000   1.4446   0.08189   0.07580  -0.0677   0.0476   1.0000
  16.250   1.4373   0.08663   0.08063  -0.0690   0.0446   1.0000
  16.500   1.4280   0.09181   0.08588  -0.0707   0.0422   1.0000
  16.750   1.4233   0.09635   0.09054  -0.0722   0.0395   1.0000
  17.000   1.4160   0.10137   0.09566  -0.0740   0.0371   1.0000
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