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EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 584 AIRFOIL (e584-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.98 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e584-il-1000000.txt
Download as CSV file: xf-e584-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 584 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0588   0.08964   0.08643  -0.1217   0.6949   0.0110
 -11.250  -0.0533   0.08716   0.08395  -0.1228   0.6926   0.0112
 -11.000  -0.0536   0.08338   0.08017  -0.1243   0.6905   0.0113
 -10.750  -0.0503   0.08048   0.07727  -0.1255   0.6883   0.0116
 -10.500  -0.0538   0.07621   0.07301  -0.1273   0.6864   0.0116
 -10.250  -0.0543   0.07271   0.06951  -0.1289   0.6844   0.0119
 -10.000  -0.0665   0.06684   0.06366  -0.1319   0.6828   0.0118
  -9.750  -0.0834   0.05968   0.05653  -0.1377   0.6812   0.0119
  -9.500  -0.0783   0.04095   0.03791  -0.1331   0.6776   0.0128
  -9.250  -0.0998   0.03710   0.03400  -0.1336   0.6763   0.0126
  -9.000  -0.1279   0.03288   0.02968  -0.1319   0.6750   0.0126
  -8.750  -0.1509   0.02988   0.02656  -0.1285   0.6735   0.0126
  -8.500  -0.2035   0.02463   0.02077  -0.1197   0.6721   0.0133
  -8.250  -0.2251   0.02004   0.01594  -0.1152   0.6705   0.0136
  -8.000  -0.2153   0.01854   0.01438  -0.1136   0.6687   0.0138
  -7.750  -0.2053   0.01718   0.01292  -0.1120   0.6670   0.0139
  -7.500  -0.1941   0.01583   0.01148  -0.1103   0.6660   0.0141
  -7.250  -0.1821   0.01444   0.00996  -0.1086   0.6648   0.0144
  -7.000  -0.1953   0.01811   0.01211  -0.1053   0.6653   0.0083
  -6.750  -0.1729   0.01674   0.01066  -0.1046   0.6641   0.0080
  -6.500  -0.1504   0.01556   0.00935  -0.1039   0.6628   0.0078
  -6.250  -0.1274   0.01458   0.00825  -0.1031   0.6613   0.0076
  -6.000  -0.1041   0.01387   0.00746  -0.1024   0.6597   0.0075
  -5.750  -0.0809   0.01325   0.00675  -0.1017   0.6580   0.0074
  -5.500  -0.0575   0.01274   0.00618  -0.1010   0.6564   0.0074
  -5.250  -0.0338   0.01231   0.00568  -0.1004   0.6546   0.0075
  -5.000  -0.0092   0.01198   0.00528  -0.1000   0.6526   0.0075
  -4.750   0.0146   0.01159   0.00487  -0.0994   0.6514   0.0077
  -4.500   0.0390   0.01127   0.00453  -0.0988   0.6499   0.0079
  -4.250   0.0641   0.01101   0.00424  -0.0984   0.6482   0.0081
  -4.000   0.0885   0.01067   0.00387  -0.0979   0.6464   0.0088
  -3.750   0.1143   0.01048   0.00365  -0.0977   0.6447   0.0099
  -3.500   0.1400   0.01025   0.00341  -0.0974   0.6429   0.0136
  -3.250   0.1645   0.00995   0.00321  -0.0970   0.6411   0.0377
  -3.000   0.1909   0.00980   0.00315  -0.0970   0.6389   0.0638
  -2.750   0.2163   0.00958   0.00306  -0.0968   0.6374   0.0964
  -2.500   0.2410   0.00929   0.00295  -0.0964   0.6359   0.1443
  -2.250   0.2635   0.00878   0.00284  -0.0959   0.6341   0.2549
  -2.000   0.2822   0.00781   0.00266  -0.0951   0.6322   0.4882
  -1.750   0.3014   0.00692   0.00273  -0.0938   0.6303   0.7696
  -1.500   0.3301   0.00705   0.00284  -0.0939   0.6285   0.7944
  -1.250   0.3594   0.00719   0.00290  -0.0943   0.6267   0.8067
  -1.000   0.3874   0.00744   0.00313  -0.0942   0.6246   0.8159
  -0.750   0.4160   0.00756   0.00321  -0.0944   0.6230   0.8230
  -0.500   0.4425   0.00763   0.00331  -0.0941   0.6212   0.8277
  -0.250   0.4697   0.00773   0.00341  -0.0939   0.6190   0.8322
   0.000   0.4978   0.00785   0.00350  -0.0940   0.6169   0.8376
   0.250   0.5226   0.00802   0.00369  -0.0931   0.6149   0.8443
   0.500   0.5468   0.00835   0.00403  -0.0919   0.6129   0.8537
   0.750   0.5706   0.00852   0.00419  -0.0908   0.6108   0.8595
   1.000   0.5969   0.00855   0.00422  -0.0905   0.6087   0.8614
   1.250   0.6242   0.00852   0.00420  -0.0906   0.6063   0.8627
   1.500   0.6518   0.00849   0.00416  -0.0908   0.6036   0.8639
   1.750   0.6797   0.00845   0.00411  -0.0910   0.6010   0.8649
   2.000   0.7076   0.00841   0.00406  -0.0913   0.5984   0.8660
   2.250   0.7359   0.00841   0.00402  -0.0917   0.5957   0.8668
   2.500   0.7639   0.00837   0.00401  -0.0920   0.5927   0.8677
   2.750   0.7919   0.00834   0.00398  -0.0923   0.5891   0.8686
   3.000   0.8196   0.00830   0.00393  -0.0926   0.5854   0.8693
   3.250   0.8470   0.00831   0.00390  -0.0928   0.5815   0.8699
   3.500   0.8749   0.00831   0.00392  -0.0932   0.5775   0.8707
   3.750   0.9024   0.00831   0.00393  -0.0935   0.5731   0.8711
   4.000   0.9291   0.00835   0.00393  -0.0936   0.5686   0.8715
   4.250   0.9562   0.00837   0.00395  -0.0938   0.5641   0.8719
   4.500   0.9828   0.00835   0.00395  -0.0939   0.5593   0.8725
   4.750   1.0081   0.00839   0.00397  -0.0937   0.5541   0.8731
   5.000   1.0335   0.00843   0.00402  -0.0935   0.5491   0.8738
   5.250   1.0592   0.00846   0.00408  -0.0934   0.5436   0.8744
   5.500   1.0833   0.00854   0.00414  -0.0930   0.5375   0.8750
   5.750   1.1085   0.00860   0.00422  -0.0928   0.5315   0.8755
   6.000   1.1326   0.00867   0.00430  -0.0924   0.5241   0.8760
   6.250   1.1559   0.00876   0.00439  -0.0919   0.5172   0.8766
   6.500   1.1787   0.00884   0.00448  -0.0912   0.5087   0.8772
   6.750   1.1991   0.00895   0.00458  -0.0901   0.5003   0.8779
   7.000   1.2175   0.00909   0.00470  -0.0886   0.4900   0.8787
   7.250   1.2371   0.00924   0.00485  -0.0873   0.4796   0.8794
   7.500   1.2547   0.00946   0.00505  -0.0857   0.4682   0.8802
   7.750   1.2705   0.00973   0.00529  -0.0838   0.4554   0.8812
   8.000   1.2871   0.01001   0.00555  -0.0821   0.4438   0.8823
   8.250   1.3037   0.01030   0.00582  -0.0804   0.4310   0.8831
   8.500   1.3184   0.01063   0.00613  -0.0784   0.4182   0.8839
   8.750   1.3316   0.01103   0.00649  -0.0762   0.4040   0.8848
   9.000   1.3430   0.01148   0.00691  -0.0738   0.3893   0.8856
   9.250   1.3528   0.01201   0.00739  -0.0711   0.3735   0.8864
   9.500   1.3606   0.01263   0.00796  -0.0683   0.3566   0.8872
   9.750   1.3676   0.01328   0.00857  -0.0654   0.3409   0.8884
  10.000   1.3738   0.01401   0.00926  -0.0626   0.3262   0.8896
  10.250   1.3781   0.01487   0.01009  -0.0595   0.3105   0.8909
  10.500   1.3803   0.01590   0.01107  -0.0564   0.2932   0.8922
  10.750   1.3818   0.01705   0.01217  -0.0534   0.2765   0.8935
  11.000   1.3819   0.01836   0.01343  -0.0505   0.2593   0.8950
  11.250   1.3831   0.01971   0.01474  -0.0478   0.2438   0.8966
  11.500   1.3845   0.02114   0.01612  -0.0454   0.2288   0.8980
  11.750   1.3870   0.02258   0.01754  -0.0432   0.2154   0.8993
  12.000   1.3889   0.02412   0.01904  -0.0412   0.2021   0.9005
  12.250   1.3908   0.02574   0.02062  -0.0393   0.1892   0.9016
  12.500   1.3922   0.02745   0.02229  -0.0374   0.1764   0.9026
  12.750   1.3928   0.02925   0.02405  -0.0357   0.1628   0.9042
  13.000   1.3941   0.03106   0.02584  -0.0341   0.1502   0.9058
  13.250   1.3935   0.03310   0.02783  -0.0325   0.1360   0.9073
  13.500   1.3929   0.03520   0.02988  -0.0310   0.1221   0.9089
  13.750   1.3950   0.03713   0.03178  -0.0298   0.1112   0.9104
  14.000   1.3980   0.03904   0.03369  -0.0288   0.1017   0.9120
  14.250   1.3929   0.04167   0.03622  -0.0274   0.0857   0.9136
  14.500   1.3958   0.04371   0.03825  -0.0265   0.0774   0.9151
  14.750   1.4004   0.04566   0.04021  -0.0259   0.0711   0.9166
  15.000   1.3996   0.04814   0.04265  -0.0251   0.0611   0.9182
  15.250   1.4014   0.05040   0.04492  -0.0245   0.0551   0.9204
  15.500   1.4037   0.05266   0.04720  -0.0239   0.0487   0.9226
  15.750   1.4056   0.05505   0.04961  -0.0235   0.0432   0.9249
  16.000   1.4069   0.05755   0.05211  -0.0232   0.0376   0.9274
  16.250   1.4077   0.06020   0.05479  -0.0230   0.0333   0.9302
  16.500   1.4100   0.06269   0.05731  -0.0228   0.0292   0.9336
  16.750   1.4111   0.06532   0.06000  -0.0227   0.0258   0.9385
  17.000   1.4124   0.06799   0.06272  -0.0226   0.0231   0.9446
  17.250   1.4146   0.07073   0.06554  -0.0229   0.0206   0.9571
  17.500   1.4203   0.07383   0.06870  -0.0244   0.0184   0.9768
  17.750   1.4195   0.07687   0.07177  -0.0247   0.0161   1.0000
  18.000   1.4214   0.07987   0.07484  -0.0253   0.0148   1.0000
  18.250   1.4214   0.08314   0.07816  -0.0260   0.0132   1.0000
  18.500   1.4228   0.08629   0.08137  -0.0267   0.0122   1.0000
  18.750   1.4212   0.08987   0.08500  -0.0276   0.0109   1.0000
  19.000   1.4224   0.09308   0.08828  -0.0285   0.0099   1.0000
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