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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 500,000
Max Cl/Cd: 121.97 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e434-il-500000.txt
Download as CSV file: xf-e434-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1045   0.08446   0.08194  -0.1019   0.9128   0.0158
  -9.500  -0.1005   0.07893   0.07631  -0.1075   0.8898   0.0161
  -9.250  -0.1003   0.07463   0.07193  -0.1102   0.8731   0.0162
  -9.000  -0.1015   0.07045   0.06770  -0.1127   0.8599   0.0162
  -8.750  -0.1058   0.06592   0.06311  -0.1154   0.8488   0.0163
  -8.500  -0.1073   0.06358   0.06076  -0.1152   0.8395   0.0165
  -8.250  -0.1210   0.05841   0.05552  -0.1190   0.8295   0.0165
  -8.000  -0.1307   0.05585   0.05289  -0.1181   0.8216   0.0166
  -7.750  -0.1336   0.05296   0.04992  -0.1180   0.8149   0.0167
  -7.500  -0.1319   0.05071   0.04761  -0.1176   0.8088   0.0169
  -7.250  -0.1293   0.04790   0.04466  -0.1173   0.8035   0.0172
  -7.000  -0.1246   0.04501   0.04166  -0.1169   0.7981   0.0175
  -6.750  -0.1181   0.04198   0.03848  -0.1162   0.7932   0.0181
  -6.500  -0.1152   0.03712   0.03294  -0.1138   0.7886   0.0201
  -6.250  -0.1074   0.03325   0.02900  -0.1130   0.7843   0.0206
  -4.750   0.0026   0.01871   0.01271  -0.1059   0.7615   0.0174
  -4.500   0.0279   0.01490   0.00816  -0.1036   0.7585   0.0103
  -4.250   0.0537   0.01411   0.00722  -0.1032   0.7552   0.0102
  -4.000   0.0779   0.01315   0.00622  -0.1025   0.7515   0.0104
  -3.750   0.1029   0.01251   0.00554  -0.1020   0.7479   0.0107
  -3.500   0.1285   0.01201   0.00500  -0.1017   0.7446   0.0115
  -3.250   0.1550   0.01167   0.00456  -0.1014   0.7415   0.0128
  -3.000   0.1802   0.01121   0.00411  -0.1010   0.7380   0.0148
  -2.750   0.2064   0.01087   0.00375  -0.1007   0.7344   0.0193
  -2.500   0.2311   0.01023   0.00337  -0.1003   0.7309   0.0735
  -2.250   0.2564   0.00975   0.00321  -0.1002   0.7277   0.1689
  -2.000   0.2795   0.00902   0.00310  -0.1000   0.7244   0.3561
  -1.750   0.2950   0.00775   0.00315  -0.0981   0.7206   0.7253
  -1.500   0.3190   0.00780   0.00332  -0.0968   0.7170   0.8053
  -1.250   0.3451   0.00790   0.00337  -0.0962   0.7136   0.8291
  -1.000   0.3713   0.00806   0.00345  -0.0956   0.7104   0.8463
  -0.750   0.3960   0.00815   0.00354  -0.0947   0.7067   0.8603
  -0.500   0.4212   0.00824   0.00361  -0.0939   0.7027   0.8726
  -0.250   0.4455   0.00832   0.00365  -0.0929   0.6990   0.8815
   0.000   0.4712   0.00842   0.00367  -0.0923   0.6957   0.8900
   0.250   0.4932   0.00852   0.00378  -0.0907   0.6917   0.9017
   0.500   0.5102   0.00861   0.00389  -0.0878   0.6874   0.9167
   0.750   0.5277   0.00863   0.00390  -0.0850   0.6835   0.9286
   1.000   0.5525   0.00866   0.00386  -0.0843   0.6798   0.9346
   1.250   0.5770   0.00862   0.00383  -0.0837   0.6752   0.9381
   1.500   0.6035   0.00860   0.00379  -0.0835   0.6705   0.9414
   1.750   0.6309   0.00860   0.00373  -0.0836   0.6664   0.9444
   2.000   0.6578   0.00860   0.00371  -0.0836   0.6619   0.9470
   2.250   0.6837   0.00856   0.00369  -0.0833   0.6567   0.9498
   2.500   0.7107   0.00854   0.00364  -0.0833   0.6520   0.9526
   2.750   0.7377   0.00856   0.00364  -0.0833   0.6472   0.9555
   3.000   0.7630   0.00854   0.00364  -0.0830   0.6414   0.9590
   3.250   0.7906   0.00853   0.00361  -0.0831   0.6361   0.9618
   3.500   0.8182   0.00854   0.00363  -0.0833   0.6303   0.9648
   3.750   0.8452   0.00854   0.00364  -0.0833   0.6238   0.9683
   4.000   0.8723   0.00857   0.00364  -0.0834   0.6177   0.9718
   4.250   0.9019   0.00858   0.00371  -0.0840   0.6102   0.9746
   4.500   0.9327   0.00865   0.00374  -0.0850   0.6034   0.9772
   4.750   0.9627   0.00868   0.00382  -0.0857   0.5949   0.9808
   5.000   0.9932   0.00876   0.00390  -0.0866   0.5868   0.9842
   5.250   1.0263   0.00885   0.00400  -0.0881   0.5771   0.9865
   5.500   1.0585   0.00895   0.00412  -0.0895   0.5664   0.9893
   5.750   1.0899   0.00907   0.00425  -0.0906   0.5552   0.9928
   6.000   1.1215   0.00923   0.00440  -0.0919   0.5428   0.9967
   6.250   1.1441   0.00938   0.00455  -0.0913   0.5298   1.0000
   6.500   1.1577   0.00953   0.00469  -0.0889   0.5162   1.0000
   6.750   1.1771   0.00974   0.00488  -0.0877   0.5004   1.0000
   7.000   1.1971   0.01001   0.00512  -0.0866   0.4825   1.0000
   7.250   1.2167   0.01032   0.00539  -0.0855   0.4626   1.0000
   7.500   1.2338   0.01071   0.00571  -0.0839   0.4413   1.0000
   7.750   1.2486   0.01112   0.00606  -0.0819   0.4204   1.0000
   8.000   1.2606   0.01160   0.00646  -0.0794   0.3978   1.0000
   8.250   1.2715   0.01216   0.00694  -0.0768   0.3755   1.0000
   8.500   1.2821   0.01275   0.00746  -0.0742   0.3532   1.0000
   8.750   1.2910   0.01344   0.00807  -0.0714   0.3309   1.0000
   9.000   1.2993   0.01420   0.00874  -0.0687   0.3078   1.0000
   9.250   1.3068   0.01504   0.00950  -0.0660   0.2865   1.0000
   9.500   1.3152   0.01589   0.01029  -0.0636   0.2662   1.0000
   9.750   1.3222   0.01686   0.01119  -0.0611   0.2467   1.0000
  10.000   1.3290   0.01790   0.01216  -0.0588   0.2272   1.0000
  10.250   1.3358   0.01901   0.01320  -0.0566   0.2078   1.0000
  10.500   1.3424   0.02018   0.01432  -0.0545   0.1903   1.0000
  10.750   1.3479   0.02147   0.01554  -0.0524   0.1733   1.0000
  11.000   1.3547   0.02274   0.01677  -0.0506   0.1580   1.0000
  11.250   1.3611   0.02408   0.01806  -0.0489   0.1428   1.0000
  11.500   1.3673   0.02548   0.01943  -0.0472   0.1288   1.0000
  11.750   1.3731   0.02694   0.02086  -0.0456   0.1158   1.0000
  12.000   1.3784   0.02849   0.02239  -0.0440   0.1035   1.0000
  12.250   1.3831   0.03012   0.02399  -0.0425   0.0919   1.0000
  12.500   1.3875   0.03183   0.02567  -0.0411   0.0812   1.0000
  12.750   1.3924   0.03355   0.02738  -0.0399   0.0716   1.0000
  13.000   1.3969   0.03535   0.02919  -0.0387   0.0630   1.0000
  13.250   1.4009   0.03726   0.03110  -0.0375   0.0555   1.0000
  13.500   1.4032   0.03937   0.03321  -0.0364   0.0487   1.0000
  13.750   1.4066   0.04144   0.03530  -0.0355   0.0429   1.0000
  14.000   1.4101   0.04358   0.03749  -0.0347   0.0382   1.0000
  14.250   1.4105   0.04609   0.04001  -0.0339   0.0341   1.0000
  14.500   1.4147   0.04828   0.04228  -0.0333   0.0308   1.0000
  14.750   1.4144   0.05102   0.04504  -0.0328   0.0278   1.0000
  15.000   1.4175   0.05346   0.04757  -0.0324   0.0253   1.0000
  15.250   1.4185   0.05619   0.05035  -0.0322   0.0231   1.0000
  15.500   1.4182   0.05916   0.05339  -0.0320   0.0211   1.0000
  15.750   1.4205   0.06189   0.05622  -0.0321   0.0194   1.0000
  16.000   1.4159   0.06555   0.05992  -0.0322   0.0176   1.0000
  16.250   1.4191   0.06833   0.06282  -0.0325   0.0163   1.0000
  16.500   1.4196   0.07149   0.06604  -0.0329   0.0149   1.0000
  16.750   1.4136   0.07564   0.07027  -0.0335   0.0138   1.0000
  17.000   1.4150   0.07885   0.07360  -0.0341   0.0127   1.0000
  17.250   1.4126   0.08267   0.07752  -0.0350   0.0118   1.0000
  17.500   1.4029   0.08765   0.08258  -0.0363   0.0110   1.0000
  17.750   1.4014   0.09151   0.08658  -0.0374   0.0102   1.0000
  18.000   1.3994   0.09550   0.09066  -0.0386   0.0093   1.0000
  18.250   1.3904   0.10072   0.09598  -0.0404   0.0088   1.0000
  18.500   1.3826   0.10584   0.10121  -0.0423   0.0082   1.0000
  18.750   1.3777   0.11054   0.10605  -0.0442   0.0076   1.0000
  19.000   1.3727   0.11532   0.11094  -0.0462   0.0069   1.0000
  19.250   1.3614   0.12131   0.11702  -0.0489   0.0065   1.0000
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