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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 500,000
Max Cl/Cd: 106.89 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e582-il-500000-n5.txt
Download as CSV file: xf-e582-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0908   0.07255   0.06950  -0.1263   0.8479   0.0044
 -10.000  -0.0911   0.06920   0.06610  -0.1279   0.8362   0.0043
  -9.500  -0.1262   0.05533   0.05219  -0.1370   0.8143   0.0042
  -9.250  -0.1618   0.04788   0.04459  -0.1393   0.8039   0.0042
  -9.000  -0.1821   0.04425   0.04081  -0.1376   0.7951   0.0041
  -8.750  -0.2164   0.03832   0.03462  -0.1337   0.7873   0.0041
  -8.500  -0.2628   0.02843   0.02397  -0.1275   0.7802   0.0041
  -8.250  -0.2678   0.02390   0.01877  -0.1241   0.7753   0.0042
  -8.000  -0.2555   0.02173   0.01618  -0.1223   0.7705   0.0044
  -7.750  -0.2406   0.01989   0.01402  -0.1209   0.7660   0.0045
  -7.500  -0.2207   0.01883   0.01275  -0.1200   0.7624   0.0047
  -7.250  -0.1996   0.01786   0.01162  -0.1193   0.7587   0.0048
  -7.000  -0.1771   0.01712   0.01075  -0.1188   0.7548   0.0049
  -6.750  -0.1540   0.01643   0.00992  -0.1182   0.7511   0.0051
  -6.500  -0.1305   0.01579   0.00914  -0.1178   0.7478   0.0053
  -6.250  -0.1066   0.01516   0.00841  -0.1173   0.7446   0.0055
  -6.000  -0.0826   0.01457   0.00771  -0.1168   0.7411   0.0057
  -5.750  -0.0578   0.01415   0.00720  -0.1165   0.7376   0.0062
  -5.500  -0.0327   0.01378   0.00673  -0.1162   0.7345   0.0065
  -5.250  -0.0091   0.01319   0.00607  -0.1157   0.7317   0.0069
  -5.000   0.0159   0.01279   0.00565  -0.1155   0.7285   0.0072
  -4.750   0.0409   0.01239   0.00521  -0.1151   0.7252   0.0075
  -4.500   0.0663   0.01203   0.00479  -0.1149   0.7219   0.0079
  -4.250   0.0921   0.01173   0.00442  -0.1147   0.7190   0.0084
  -4.000   0.1182   0.01145   0.00406  -0.1145   0.7162   0.0092
  -3.750   0.1443   0.01117   0.00377  -0.1144   0.7130   0.0107
  -3.500   0.1706   0.01091   0.00350  -0.1143   0.7098   0.0143
  -3.250   0.1969   0.01066   0.00328  -0.1142   0.7067   0.0252
  -3.000   0.2231   0.01038   0.00310  -0.1142   0.7037   0.0537
  -2.750   0.2495   0.01010   0.00296  -0.1143   0.7009   0.0948
  -2.500   0.2754   0.00970   0.00284  -0.1144   0.6977   0.1667
  -2.250   0.3012   0.00923   0.00270  -0.1146   0.6943   0.2715
  -2.000   0.3275   0.00871   0.00256  -0.1150   0.6910   0.3974
  -1.750   0.3539   0.00797   0.00240  -0.1155   0.6879   0.5828
  -1.500   0.3785   0.00784   0.00272  -0.1147   0.6849   0.7282
  -1.250   0.4067   0.00794   0.00278  -0.1148   0.6813   0.7519
  -1.000   0.4344   0.00803   0.00284  -0.1148   0.6776   0.7640
  -0.750   0.4623   0.00813   0.00288  -0.1148   0.6741   0.7731
  -0.500   0.4899   0.00829   0.00297  -0.1148   0.6709   0.7858
  -0.250   0.5157   0.00849   0.00320  -0.1141   0.6671   0.8003
   0.000   0.5403   0.00864   0.00337  -0.1133   0.6630   0.8081
   0.250   0.5681   0.00869   0.00337  -0.1134   0.6591   0.8114
   0.500   0.5965   0.00873   0.00335  -0.1137   0.6553   0.8133
   0.750   0.6249   0.00874   0.00334  -0.1140   0.6506   0.8148
   1.000   0.6526   0.00876   0.00333  -0.1142   0.6457   0.8159
   1.500   0.7072   0.00882   0.00334  -0.1144   0.6361   0.8177
   1.750   0.7344   0.00886   0.00336  -0.1144   0.6309   0.8185
   2.000   0.7614   0.00891   0.00338  -0.1144   0.6262   0.8195
   2.250   0.7885   0.00895   0.00343  -0.1145   0.6204   0.8205
   2.500   0.8152   0.00900   0.00346  -0.1145   0.6142   0.8214
   2.750   0.8418   0.00906   0.00351  -0.1145   0.6080   0.8222
   3.000   0.8682   0.00912   0.00356  -0.1144   0.6008   0.8231
   3.250   0.8943   0.00920   0.00363  -0.1143   0.5941   0.8241
   3.500   0.9203   0.00928   0.00370  -0.1142   0.5862   0.8253
   3.750   0.9459   0.00938   0.00378  -0.1140   0.5788   0.8264
   4.000   0.9712   0.00948   0.00388  -0.1138   0.5699   0.8273
   4.250   0.9963   0.00959   0.00398  -0.1135   0.5611   0.8282
   4.500   1.0202   0.00973   0.00409  -0.1130   0.5512   0.8291
   4.750   1.0445   0.00986   0.00422  -0.1126   0.5403   0.8300
   5.000   1.0676   0.01002   0.00436  -0.1119   0.5286   0.8308
   5.250   1.0892   0.01019   0.00452  -0.1109   0.5156   0.8317
   5.500   1.1098   0.01039   0.00470  -0.1098   0.5020   0.8326
   5.750   1.1291   0.01062   0.00491  -0.1084   0.4870   0.8338
   6.000   1.1463   0.01087   0.00513  -0.1066   0.4712   0.8350
   6.250   1.1616   0.01115   0.00537  -0.1044   0.4546   0.8363
   6.500   1.1759   0.01150   0.00567  -0.1021   0.4365   0.8375
   6.750   1.1893   0.01191   0.00603  -0.0997   0.4183   0.8389
   7.000   1.2028   0.01235   0.00642  -0.0974   0.4000   0.8403
   7.250   1.2153   0.01284   0.00685  -0.0950   0.3800   0.8417
   7.500   1.2264   0.01340   0.00735  -0.0924   0.3597   0.8432
   7.750   1.2370   0.01402   0.00790  -0.0899   0.3402   0.8447
   8.000   1.2481   0.01464   0.00847  -0.0875   0.3216   0.8461
   8.250   1.2584   0.01529   0.00909  -0.0851   0.3039   0.8475
   8.500   1.2680   0.01601   0.00977  -0.0826   0.2862   0.8490
   8.750   1.2765   0.01683   0.01054  -0.0801   0.2683   0.8508
   9.000   1.2854   0.01768   0.01136  -0.0778   0.2515   0.8528
   9.250   1.2941   0.01859   0.01223  -0.0756   0.2342   0.8548
   9.500   1.3020   0.01960   0.01319  -0.0734   0.2162   0.8567
   9.750   1.3089   0.02072   0.01425  -0.0712   0.1979   0.8587
  10.000   1.3167   0.02186   0.01533  -0.0692   0.1819   0.8605
  10.500   1.3303   0.02429   0.01771  -0.0653   0.1503   0.8644
  10.750   1.3372   0.02558   0.01897  -0.0635   0.1358   0.8666
  11.000   1.3449   0.02686   0.02024  -0.0619   0.1241   0.8690
  11.250   1.3515   0.02827   0.02162  -0.0603   0.1113   0.8715
  11.500   1.3585   0.02969   0.02303  -0.0588   0.1000   0.8740
  11.750   1.3652   0.03116   0.02451  -0.0573   0.0888   0.8766
  12.000   1.3706   0.03274   0.02609  -0.0559   0.0777   0.8796
  12.250   1.3759   0.03440   0.02774  -0.0545   0.0678   0.8829
  12.500   1.3799   0.03622   0.02954  -0.0531   0.0572   0.8868
  13.000   1.3869   0.04004   0.03336  -0.0506   0.0393   0.8961
  13.250   1.3909   0.04199   0.03534  -0.0495   0.0331   0.9022
  13.500   1.3939   0.04409   0.03745  -0.0485   0.0268   0.9093
  14.000   1.3993   0.04846   0.04194  -0.0467   0.0175   0.9424
  14.250   1.4022   0.05073   0.04425  -0.0461   0.0140   1.0000
  14.500   1.4083   0.05289   0.04648  -0.0458   0.0125   1.0000
  14.750   1.4120   0.05535   0.04899  -0.0455   0.0106   1.0000
  15.000   1.4166   0.05777   0.05148  -0.0454   0.0092   1.0000
  15.250   1.4196   0.06042   0.05419  -0.0453   0.0076   1.0000
  15.500   1.4231   0.06308   0.05692  -0.0453   0.0065   1.0000
  15.750   1.4255   0.06592   0.05985  -0.0453   0.0057   1.0000
  16.000   1.4283   0.06876   0.06277  -0.0455   0.0049   1.0000
  16.250   1.4290   0.07193   0.06602  -0.0458   0.0041   1.0000
  16.500   1.4300   0.07514   0.06933  -0.0462   0.0035   1.0000
  16.750   1.4302   0.07852   0.07280  -0.0468   0.0031   1.0000
  17.000   1.4291   0.08213   0.07650  -0.0474   0.0026   1.0000
  17.250   1.4288   0.08569   0.08017  -0.0482   0.0023   1.0000
  17.500   1.4265   0.08961   0.08419  -0.0491   0.0020   1.0000
  17.750   1.4237   0.09370   0.08839  -0.0502   0.0018   1.0000
  18.000   1.4207   0.09787   0.09268  -0.0515   0.0015   1.0000
  18.250   1.4172   0.10217   0.09709  -0.0529   0.0014   1.0000
  18.500   1.4128   0.10669   0.10174  -0.0544   0.0012   1.0000
  18.750   1.4077   0.11139   0.10656  -0.0562   0.0011   1.0000
  19.000   1.4019   0.11628   0.11157  -0.0582   0.0010   1.0000
  19.250   1.3959   0.12126   0.11667  -0.0603   0.0009   1.0000
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