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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 500,000
Max Cl/Cd: 100.67 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e562-il-500000-n5.txt
Download as CSV file: xf-e562-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.6471   0.14313   0.14020  -0.0315   1.0000   0.0082
 -17.500  -0.6638   0.13534   0.13233  -0.0351   1.0000   0.0083
 -17.250  -0.6813   0.12773   0.12460  -0.0386   1.0000   0.0082
 -17.000  -0.6923   0.12158   0.11840  -0.0414   1.0000   0.0084
 -16.750  -0.7046   0.11535   0.11209  -0.0443   1.0000   0.0085
 -16.500  -0.7163   0.10948   0.10614  -0.0469   1.0000   0.0085
 -16.250  -0.7274   0.10384   0.10042  -0.0494   1.0000   0.0085
 -16.000  -0.7378   0.09847   0.09498  -0.0519   1.0000   0.0085
 -15.750  -0.7467   0.09340   0.08983  -0.0541   1.0000   0.0086
 -15.500  -0.7565   0.08831   0.08467  -0.0564   1.0000   0.0088
 -15.250  -0.7648   0.08360   0.07990  -0.0585   1.0000   0.0088
 -15.000  -0.7743   0.07891   0.07513  -0.0605   1.0000   0.0088
 -14.750  -0.7832   0.07436   0.07051  -0.0625   1.0000   0.0090
 -14.500  -0.7922   0.07000   0.06608  -0.0642   1.0000   0.0090
 -14.250  -0.8017   0.06575   0.06175  -0.0659   1.0000   0.0092
 -14.000  -0.8117   0.06168   0.05761  -0.0673   1.0000   0.0093
 -13.750  -0.8219   0.05783   0.05369  -0.0685   1.0000   0.0094
 -13.500  -0.8340   0.05396   0.04975  -0.0696   1.0000   0.0094
 -13.250  -0.8445   0.05044   0.04616  -0.0703   1.0000   0.0096
 -13.000  -0.8586   0.04684   0.04249  -0.0707   1.0000   0.0096
 -12.750  -0.8736   0.04341   0.03900  -0.0707   1.0000   0.0096
 -12.500  -0.8798   0.03993   0.03543  -0.0725   0.9990   0.0098
 -12.250  -0.8687   0.03623   0.03161  -0.0779   0.9955   0.0099
 -12.000  -0.8594   0.03269   0.02793  -0.0829   0.9909   0.0101
 -11.750  -0.8395   0.02877   0.02385  -0.0905   0.9862   0.0104
 -11.500  -0.8090   0.02577   0.02071  -0.0979   0.9836   0.0107
 -11.250  -0.7897   0.02415   0.01901  -0.0995   0.9782   0.0110
 -11.000  -0.7617   0.02290   0.01766  -0.1019   0.9751   0.0115
 -10.750  -0.7308   0.02175   0.01643  -0.1045   0.9730   0.0120
 -10.500  -0.7091   0.02077   0.01536  -0.1048   0.9676   0.0126
 -10.250  -0.6808   0.01989   0.01438  -0.1061   0.9638   0.0131
 -10.000  -0.6499   0.01884   0.01328  -0.1082   0.9613   0.0139
  -9.750  -0.6272   0.01812   0.01252  -0.1081   0.9551   0.0147
  -9.500  -0.5978   0.01741   0.01173  -0.1092   0.9509   0.0156
  -9.250  -0.5654   0.01674   0.01098  -0.1108   0.9481   0.0165
  -9.000  -0.5425   0.01598   0.01018  -0.1105   0.9404   0.0174
  -8.750  -0.5118   0.01534   0.00949  -0.1117   0.9362   0.0185
  -8.500  -0.4827   0.01478   0.00886  -0.1123   0.9307   0.0196
  -8.250  -0.4527   0.01418   0.00821  -0.1132   0.9244   0.0210
  -8.000  -0.4176   0.01359   0.00758  -0.1150   0.9204   0.0231
  -7.750  -0.3852   0.01308   0.00702  -0.1162   0.9133   0.0252
  -7.500  -0.3471   0.01252   0.00642  -0.1187   0.9075   0.0288
  -7.250  -0.3066   0.01196   0.00586  -0.1216   0.9008   0.0354
  -7.000  -0.2626   0.01136   0.00529  -0.1254   0.8926   0.0492
  -6.750  -0.2159   0.01080   0.00477  -0.1299   0.8830   0.0699
  -6.500  -0.1724   0.01033   0.00433  -0.1335   0.8698   0.0923
  -6.250  -0.1347   0.00999   0.00397  -0.1358   0.8534   0.1126
  -6.000  -0.1018   0.00968   0.00365  -0.1371   0.8355   0.1352
  -5.750  -0.0718   0.00947   0.00342  -0.1377   0.8174   0.1565
  -5.500  -0.0434   0.00929   0.00321  -0.1379   0.7997   0.1797
  -5.250  -0.0158   0.00915   0.00305  -0.1378   0.7827   0.2008
  -5.000   0.0113   0.00906   0.00292  -0.1377   0.7661   0.2181
  -4.750   0.0382   0.00899   0.00280  -0.1375   0.7503   0.2337
  -4.500   0.0651   0.00895   0.00270  -0.1372   0.7351   0.2469
  -4.250   0.0920   0.00891   0.00261  -0.1370   0.7204   0.2605
  -4.000   0.1188   0.00889   0.00253  -0.1367   0.7061   0.2702
  -3.750   0.1456   0.00890   0.00245  -0.1364   0.6922   0.2784
  -3.500   0.1725   0.00889   0.00239  -0.1361   0.6787   0.2874
  -3.250   0.1996   0.00890   0.00232  -0.1358   0.6655   0.2948
  -3.000   0.2266   0.00890   0.00228  -0.1356   0.6527   0.3036
  -2.750   0.2537   0.00891   0.00225  -0.1354   0.6405   0.3142
  -2.500   0.2806   0.00894   0.00222  -0.1351   0.6285   0.3244
  -2.250   0.3077   0.00896   0.00220  -0.1349   0.6163   0.3322
  -2.000   0.3350   0.00899   0.00217  -0.1346   0.6048   0.3393
  -1.750   0.3621   0.00902   0.00217  -0.1344   0.5939   0.3468
  -1.500   0.3891   0.00908   0.00216  -0.1341   0.5826   0.3549
  -1.250   0.4164   0.00911   0.00217  -0.1340   0.5718   0.3619
  -1.000   0.4435   0.00916   0.00218  -0.1337   0.5619   0.3692
  -0.750   0.4706   0.00922   0.00220  -0.1335   0.5514   0.3767
  -0.500   0.4979   0.00927   0.00223  -0.1333   0.5415   0.3848
  -0.250   0.5247   0.00935   0.00226  -0.1330   0.5320   0.3918
   0.000   0.5521   0.00940   0.00231  -0.1328   0.5225   0.3998
   0.250   0.5791   0.00948   0.00235  -0.1326   0.5135   0.4074
   0.500   0.6061   0.00955   0.00241  -0.1324   0.5040   0.4149
   0.750   0.6331   0.00963   0.00246  -0.1321   0.4957   0.4229
   1.000   0.6599   0.00971   0.00254  -0.1319   0.4867   0.4304
   1.250   0.6870   0.00980   0.00261  -0.1316   0.4785   0.4382
   1.500   0.7136   0.00989   0.00269  -0.1313   0.4701   0.4458
   1.750   0.7406   0.00998   0.00278  -0.1311   0.4622   0.4539
   2.000   0.7670   0.01008   0.00287  -0.1308   0.4539   0.4613
   2.250   0.7938   0.01017   0.00297  -0.1305   0.4463   0.4699
   2.500   0.8202   0.01028   0.00308  -0.1302   0.4383   0.4779
   2.750   0.8468   0.01039   0.00319  -0.1299   0.4311   0.4866
   3.000   0.8730   0.01050   0.00332  -0.1296   0.4234   0.4954
   3.250   0.8993   0.01062   0.00345  -0.1292   0.4165   0.5050
   3.500   0.9256   0.01073   0.00358  -0.1289   0.4091   0.5145
   3.750   0.9514   0.01086   0.00374  -0.1285   0.4024   0.5250
   4.000   0.9776   0.01097   0.00388  -0.1281   0.3953   0.5363
   4.500   1.0290   0.01124   0.00422  -0.1273   0.3815   0.5611
   4.750   1.0542   0.01139   0.00440  -0.1268   0.3746   0.5752
   5.000   1.0797   0.01152   0.00459  -0.1263   0.3680   0.5913
   5.250   1.1047   0.01167   0.00479  -0.1258   0.3605   0.6087
   5.500   1.1294   0.01182   0.00500  -0.1252   0.3538   0.6285
   5.750   1.1542   0.01197   0.00522  -0.1246   0.3460   0.6515
   6.000   1.1781   0.01214   0.00546  -0.1239   0.3387   0.6770
   6.250   1.2020   0.01229   0.00570  -0.1232   0.3302   0.7073
   6.500   1.2249   0.01245   0.00596  -0.1222   0.3224   0.7449
   6.750   1.2468   0.01259   0.00622  -0.1210   0.3139   0.7917
   7.000   1.2638   0.01266   0.00647  -0.1188   0.3064   0.8625
   7.250   1.2805   0.01272   0.00664  -0.1164   0.2977   1.0000
   7.500   1.3023   0.01301   0.00691  -0.1154   0.2886   1.0000
   7.750   1.3225   0.01335   0.00722  -0.1140   0.2786   1.0000
   8.000   1.3435   0.01367   0.00753  -0.1129   0.2680   1.0000
   8.250   1.3634   0.01402   0.00787  -0.1115   0.2577   1.0000
   8.500   1.3824   0.01443   0.00824  -0.1100   0.2465   1.0000
   8.750   1.4009   0.01486   0.00864  -0.1085   0.2351   1.0000
   9.000   1.4192   0.01529   0.00905  -0.1069   0.2236   1.0000
   9.250   1.4362   0.01578   0.00952  -0.1052   0.2114   1.0000
   9.500   1.4519   0.01634   0.01003  -0.1033   0.1979   1.0000
   9.750   1.4658   0.01699   0.01062  -0.1012   0.1827   1.0000
  10.000   1.4781   0.01773   0.01129  -0.0989   0.1661   1.0000
  10.250   1.4887   0.01856   0.01204  -0.0965   0.1497   1.0000
  10.500   1.4988   0.01942   0.01284  -0.0940   0.1352   1.0000
  10.750   1.5090   0.02029   0.01368  -0.0916   0.1229   1.0000
  11.000   1.5185   0.02121   0.01458  -0.0893   0.1120   1.0000
  11.250   1.5268   0.02223   0.01557  -0.0869   0.1017   1.0000
  11.500   1.5340   0.02335   0.01668  -0.0845   0.0925   1.0000
  11.750   1.5405   0.02455   0.01788  -0.0822   0.0837   1.0000
  12.000   1.5474   0.02579   0.01912  -0.0801   0.0762   1.0000
  12.250   1.5516   0.02726   0.02059  -0.0779   0.0688   1.0000
  12.500   1.5545   0.02890   0.02223  -0.0758   0.0612   1.0000
  12.750   1.5586   0.03055   0.02390  -0.0740   0.0552   1.0000
  13.000   1.5603   0.03248   0.02584  -0.0723   0.0494   1.0000
  13.250   1.5626   0.03446   0.02786  -0.0708   0.0447   1.0000
  13.500   1.5637   0.03664   0.03008  -0.0695   0.0403   1.0000
  13.750   1.5647   0.03895   0.03244  -0.0684   0.0368   1.0000
  14.000   1.5652   0.04142   0.03497  -0.0675   0.0339   1.0000
  14.250   1.5654   0.04404   0.03764  -0.0668   0.0309   1.0000
  14.500   1.5639   0.04695   0.04062  -0.0663   0.0287   1.0000
  14.750   1.5636   0.04983   0.04357  -0.0660   0.0267   1.0000
  15.000   1.5615   0.05304   0.04686  -0.0659   0.0248   1.0000
  15.250   1.5584   0.05649   0.05038  -0.0660   0.0232   1.0000
  15.500   1.5564   0.05991   0.05390  -0.0662   0.0217   1.0000
  15.750   1.5521   0.06372   0.05780  -0.0667   0.0203   1.0000
  16.000   1.5465   0.06785   0.06201  -0.0673   0.0191   1.0000
  16.250   1.5431   0.07177   0.06603  -0.0681   0.0182   1.0000
  16.500   1.5381   0.07600   0.07035  -0.0690   0.0171   1.0000
  16.750   1.5322   0.08048   0.07493  -0.0702   0.0162   1.0000
  17.000   1.5254   0.08519   0.07973  -0.0715   0.0154   1.0000
  17.250   1.5205   0.08970   0.08434  -0.0729   0.0146   1.0000
  17.500   1.5145   0.09444   0.08918  -0.0745   0.0139   1.0000
  17.750   1.5079   0.09936   0.09420  -0.0762   0.0132   1.0000
  18.000   1.5007   0.10446   0.09939  -0.0781   0.0126   1.0000
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