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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.06 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e434-il-1000000.txt
Download as CSV file: xf-e434-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 434 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0988   0.08506   0.08269  -0.1030   0.8385   0.0083
  -9.750  -0.0969   0.08194   0.07953  -0.1040   0.8273   0.0085
  -9.500  -0.0951   0.07887   0.07642  -0.1050   0.8176   0.0086
  -9.250  -0.0943   0.07556   0.07309  -0.1063   0.8090   0.0087
  -9.000  -0.0945   0.07217   0.06967  -0.1076   0.8016   0.0089
  -8.750  -0.0956   0.06864   0.06614  -0.1092   0.7943   0.0089
  -8.500  -0.1005   0.06465   0.06213  -0.1111   0.7876   0.0091
  -8.250  -0.1089   0.06037   0.05787  -0.1142   0.7808   0.0089
  -8.000  -0.1272   0.05625   0.05370  -0.1158   0.7739   0.0089
  -7.750  -0.1367   0.05254   0.04994  -0.1161   0.7687   0.0089
  -7.500  -0.1421   0.04819   0.04549  -0.1164   0.7636   0.0092
  -7.250  -0.1437   0.04373   0.04086  -0.1160   0.7589   0.0095
  -7.000  -0.1421   0.03703   0.03386  -0.1146   0.7550   0.0099
  -6.750  -0.1461   0.01764   0.01426  -0.1061   0.7440   0.0102
  -6.500  -0.1362   0.01541   0.01191  -0.1052   0.7404   0.0104
  -6.250  -0.1213   0.01383   0.01022  -0.1045   0.7372   0.0106
  -6.000  -0.1048   0.01227   0.00852  -0.1039   0.7339   0.0108
  -5.750  -0.0877   0.01062   0.00667  -0.1030   0.7307   0.0112
  -5.500  -0.0694   0.00892   0.00467  -0.1020   0.7275   0.0121
  -5.250  -0.0522   0.00689   0.00215  -0.1007   0.7247   0.0134
  -5.000  -0.0276   0.01474   0.00908  -0.1029   0.7271   0.0076
  -4.750  -0.0044   0.01279   0.00700  -0.1021   0.7241   0.0067
  -4.500   0.0203   0.01166   0.00572  -0.1014   0.7212   0.0062
  -4.250   0.0455   0.01090   0.00485  -0.1009   0.7180   0.0060
  -4.000   0.0711   0.01036   0.00424  -0.1005   0.7148   0.0061
  -3.750   0.0971   0.00998   0.00377  -0.1002   0.7116   0.0061
  -3.500   0.1237   0.00962   0.00337  -0.1000   0.7086   0.0064
  -3.250   0.1506   0.00931   0.00303  -0.0999   0.7055   0.0068
  -3.000   0.1777   0.00906   0.00275  -0.0998   0.7024   0.0074
  -2.750   0.2047   0.00878   0.00244  -0.0997   0.6992   0.0093
  -2.500   0.2316   0.00853   0.00217  -0.0995   0.6958   0.0180
  -2.250   0.2584   0.00823   0.00202  -0.0995   0.6929   0.0553
  -2.000   0.2853   0.00795   0.00192  -0.0995   0.6896   0.1011
  -1.750   0.3112   0.00751   0.00182  -0.0996   0.6863   0.2085
  -1.500   0.3351   0.00677   0.00173  -0.0995   0.6829   0.4234
  -1.250   0.3564   0.00582   0.00173  -0.0987   0.6793   0.7385
  -1.000   0.3836   0.00577   0.00178  -0.0985   0.6761   0.7854
  -0.750   0.4116   0.00579   0.00180  -0.0985   0.6725   0.8056
  -0.500   0.4393   0.00583   0.00182  -0.0984   0.6688   0.8213
  -0.250   0.4668   0.00590   0.00185  -0.0983   0.6649   0.8322
   0.000   0.4949   0.00594   0.00188  -0.0984   0.6612   0.8417
   0.250   0.5224   0.00597   0.00191  -0.0983   0.6571   0.8486
   0.500   0.5504   0.00603   0.00193  -0.0984   0.6529   0.8560
   0.750   0.5765   0.00612   0.00201  -0.0979   0.6486   0.8651
   1.000   0.6025   0.00617   0.00209  -0.0974   0.6443   0.8760
   1.250   0.6281   0.00626   0.00218  -0.0968   0.6397   0.8856
   1.500   0.6547   0.00631   0.00220  -0.0966   0.6350   0.8900
   1.750   0.6824   0.00633   0.00222  -0.0967   0.6304   0.8922
   2.000   0.7102   0.00635   0.00224  -0.0968   0.6251   0.8942
   2.250   0.7375   0.00641   0.00226  -0.0968   0.6198   0.8965
   2.500   0.7656   0.00643   0.00229  -0.0970   0.6142   0.8986
   2.750   0.7933   0.00648   0.00231  -0.0972   0.6080   0.9006
   3.000   0.8211   0.00655   0.00236  -0.0974   0.6021   0.9025
   3.250   0.8479   0.00656   0.00238  -0.0973   0.5951   0.9047
   3.500   0.8740   0.00664   0.00243  -0.0971   0.5883   0.9070
   3.750   0.9010   0.00668   0.00249  -0.0971   0.5808   0.9092
   4.000   0.9270   0.00677   0.00257  -0.0970   0.5731   0.9116
   4.250   0.9538   0.00684   0.00264  -0.0970   0.5645   0.9141
   4.500   0.9801   0.00695   0.00272  -0.0969   0.5555   0.9165
   4.750   1.0051   0.00706   0.00281  -0.0965   0.5448   0.9190
   5.000   1.0299   0.00715   0.00291  -0.0961   0.5335   0.9218
   5.250   1.0540   0.00728   0.00302  -0.0955   0.5215   0.9250
   5.500   1.0778   0.00743   0.00316  -0.0950   0.5080   0.9284
   5.750   1.1015   0.00762   0.00331  -0.0944   0.4931   0.9316
   6.000   1.1227   0.00780   0.00346  -0.0933   0.4763   0.9354
   6.250   1.1426   0.00804   0.00365  -0.0920   0.4572   0.9398
   6.500   1.1620   0.00833   0.00387  -0.0906   0.4361   0.9448
   6.750   1.1790   0.00860   0.00409  -0.0887   0.4147   0.9508
   7.250   1.2091   0.00921   0.00459  -0.0842   0.3726   0.9711
   7.500   1.2325   0.00964   0.00493  -0.0840   0.3488   0.9910
   7.750   1.2503   0.01007   0.00528  -0.0827   0.3257   1.0000
   8.000   1.2650   0.01059   0.00569  -0.0808   0.3036   1.0000
   8.250   1.2789   0.01112   0.00613  -0.0788   0.2800   1.0000
   8.500   1.2910   0.01171   0.00662  -0.0765   0.2585   1.0000
   8.750   1.3043   0.01226   0.00710  -0.0744   0.2399   1.0000
   9.000   1.3154   0.01291   0.00766  -0.0721   0.2202   1.0000
   9.250   1.3246   0.01365   0.00832  -0.0696   0.2007   1.0000
   9.500   1.3351   0.01437   0.00897  -0.0673   0.1836   1.0000
   9.750   1.3450   0.01515   0.00969  -0.0651   0.1674   1.0000
  10.000   1.3540   0.01602   0.01049  -0.0629   0.1513   1.0000
  10.250   1.3635   0.01691   0.01133  -0.0608   0.1376   1.0000
  10.500   1.3728   0.01784   0.01222  -0.0588   0.1249   1.0000
  10.750   1.3814   0.01886   0.01320  -0.0569   0.1121   1.0000
  11.000   1.3894   0.01995   0.01424  -0.0550   0.0999   1.0000
  11.250   1.3975   0.02108   0.01534  -0.0532   0.0890   1.0000
  11.500   1.4048   0.02230   0.01652  -0.0514   0.0783   1.0000
  11.750   1.4116   0.02360   0.01778  -0.0496   0.0683   1.0000
  12.250   1.4253   0.02630   0.02044  -0.0465   0.0519   1.0000
  12.500   1.4323   0.02769   0.02183  -0.0451   0.0451   1.0000
  12.750   1.4385   0.02919   0.02331  -0.0437   0.0388   1.0000
  13.000   1.4433   0.03084   0.02494  -0.0423   0.0323   1.0000
  13.250   1.4488   0.03248   0.02658  -0.0410   0.0280   1.0000
  13.500   1.4554   0.03409   0.02821  -0.0399   0.0243   1.0000
  13.750   1.4612   0.03580   0.02994  -0.0389   0.0212   1.0000
  14.000   1.4674   0.03752   0.03170  -0.0380   0.0189   1.0000
  14.250   1.4730   0.03934   0.03355  -0.0371   0.0165   1.0000
  14.500   1.4785   0.04123   0.03547  -0.0364   0.0147   1.0000
  14.750   1.4844   0.04313   0.03742  -0.0357   0.0132   1.0000
  15.000   1.4893   0.04517   0.03951  -0.0351   0.0119   1.0000
  15.250   1.4939   0.04729   0.04168  -0.0346   0.0107   1.0000
  15.500   1.4990   0.04940   0.04386  -0.0342   0.0098   1.0000
  15.750   1.5017   0.05184   0.04634  -0.0338   0.0088   1.0000
  16.000   1.5061   0.05416   0.04874  -0.0336   0.0080   1.0000
  16.250   1.5092   0.05665   0.05130  -0.0334   0.0072   1.0000
  16.500   1.5098   0.05950   0.05421  -0.0334   0.0064   1.0000
  16.750   1.5130   0.06213   0.05692  -0.0334   0.0059   1.0000
  17.000   1.5139   0.06509   0.05994  -0.0336   0.0051   1.0000
  17.250   1.5136   0.06827   0.06320  -0.0339   0.0046   1.0000
  17.500   1.5138   0.07144   0.06646  -0.0343   0.0041   1.0000
  17.750   1.5122   0.07495   0.07005  -0.0349   0.0037   1.0000
  18.000   1.5084   0.07884   0.07402  -0.0357   0.0031   1.0000
  18.250   1.5062   0.08260   0.07789  -0.0365   0.0028   1.0000
  18.500   1.5015   0.08677   0.08214  -0.0376   0.0024   1.0000
  18.750   1.4928   0.09168   0.08716  -0.0391   0.0021   1.0000
  19.000   1.4886   0.09598   0.09157  -0.0404   0.0019   1.0000
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