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EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 431 AIRFOIL (e431-il)
Reynolds number: 500,000
Max Cl/Cd: 116.03 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e431-il-500000.txt
Download as CSV file: xf-e431-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 431 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0389   0.09819   0.09588  -0.1021   0.9427   0.0175
 -11.500  -0.0288   0.09342   0.09108  -0.1061   0.9366   0.0181
 -11.250  -0.1650   0.10523   0.10290  -0.0881   0.9636   0.0163
 -11.000  -0.1505   0.10130   0.09896  -0.0920   0.9578   0.0167
 -10.750  -0.0166   0.07522   0.07277  -0.1199   0.9125   0.0194
 -10.500  -0.0060   0.07200   0.06947  -0.1219   0.9001   0.0197
 -10.250  -0.0005   0.06870   0.06611  -0.1232   0.8879   0.0199
 -10.000   0.0025   0.06527   0.06263  -0.1245   0.8775   0.0202
  -9.750   0.0026   0.06144   0.05874  -0.1259   0.8683   0.0207
  -9.500  -0.0004   0.05730   0.05458  -0.1274   0.8597   0.0209
  -9.250  -0.0057   0.05265   0.04989  -0.1295   0.8523   0.0211
  -9.000  -0.0174   0.04687   0.04411  -0.1328   0.8449   0.0213
  -8.750  -0.0429   0.03966   0.03680  -0.1383   0.8375   0.0210
  -8.500  -0.0670   0.03536   0.03240  -0.1394   0.8298   0.0209
  -8.250  -0.0886   0.03244   0.02935  -0.1380   0.8223   0.0209
  -8.000  -0.1030   0.02984   0.02660  -0.1359   0.8161   0.0212
  -7.750  -0.1100   0.02684   0.02344  -0.1342   0.8101   0.0217
  -6.500  -0.0949   0.02083   0.01510  -0.1299   0.7956   0.0135
  -6.250  -0.0742   0.01800   0.01183  -0.1283   0.7917   0.0113
  -6.000  -0.0506   0.01620   0.00965  -0.1274   0.7881   0.0105
  -5.750  -0.0265   0.01532   0.00864  -0.1268   0.7844   0.0104
  -5.500  -0.0031   0.01455   0.00780  -0.1261   0.7806   0.0104
  -5.250   0.0207   0.01387   0.00707  -0.1256   0.7768   0.0107
  -5.000   0.0452   0.01331   0.00645  -0.1252   0.7734   0.0111
  -4.750   0.0705   0.01284   0.00591  -0.1249   0.7700   0.0119
  -4.500   0.0949   0.01244   0.00547  -0.1244   0.7664   0.0126
  -4.250   0.1194   0.01193   0.00495  -0.1241   0.7627   0.0144
  -4.000   0.1454   0.01155   0.00454  -0.1239   0.7592   0.0176
  -3.750   0.1717   0.01112   0.00412  -0.1238   0.7560   0.0311
  -3.500   0.1972   0.01066   0.00388  -0.1238   0.7528   0.0790
  -3.250   0.2222   0.01018   0.00371  -0.1239   0.7491   0.1498
  -3.000   0.2470   0.00945   0.00350  -0.1242   0.7455   0.2962
  -2.750   0.2709   0.00818   0.00333  -0.1246   0.7422   0.6069
  -2.500   0.2987   0.00823   0.00349  -0.1245   0.7391   0.6882
  -2.250   0.3265   0.00834   0.00357  -0.1244   0.7358   0.7133
  -2.000   0.3540   0.00845   0.00365  -0.1243   0.7321   0.7300
  -1.750   0.3816   0.00858   0.00375  -0.1241   0.7286   0.7437
  -1.500   0.4092   0.00872   0.00385  -0.1239   0.7254   0.7541
  -1.250   0.4384   0.00888   0.00391  -0.1241   0.7222   0.7634
  -1.000   0.4640   0.00896   0.00402  -0.1236   0.7185   0.7698
  -0.750   0.4915   0.00908   0.00410  -0.1235   0.7147   0.7793
  -0.500   0.5165   0.00926   0.00429  -0.1225   0.7111   0.7890
  -0.250   0.5434   0.00941   0.00441  -0.1221   0.7078   0.7981
   0.000   0.5691   0.00952   0.00452  -0.1216   0.7040   0.8035
   0.250   0.5965   0.00954   0.00452  -0.1217   0.6998   0.8074
   0.500   0.6256   0.00955   0.00448  -0.1222   0.6958   0.8106
   0.750   0.6542   0.00955   0.00443  -0.1224   0.6922   0.8127
   1.000   0.6813   0.00957   0.00444  -0.1224   0.6881   0.8146
   1.250   0.7080   0.00957   0.00445  -0.1224   0.6835   0.8166
   1.500   0.7357   0.00957   0.00443  -0.1225   0.6792   0.8189
   1.750   0.7649   0.00961   0.00442  -0.1230   0.6752   0.8213
   2.000   0.7917   0.00962   0.00444  -0.1230   0.6704   0.8237
   2.250   0.8195   0.00962   0.00444  -0.1232   0.6653   0.8260
   2.500   0.8477   0.00963   0.00441  -0.1235   0.6607   0.8281
   2.750   0.8736   0.00964   0.00445  -0.1233   0.6555   0.8301
   3.000   0.8995   0.00964   0.00448  -0.1230   0.6499   0.8321
   3.250   0.9270   0.00968   0.00448  -0.1231   0.6448   0.8341
   3.500   0.9528   0.00970   0.00454  -0.1230   0.6388   0.8365
   3.750   0.9790   0.00973   0.00458  -0.1229   0.6326   0.8390
   4.000   1.0065   0.00980   0.00462  -0.1230   0.6268   0.8416
   4.250   1.0313   0.00981   0.00468  -0.1226   0.6196   0.8440
   4.500   1.0567   0.00986   0.00472  -0.1223   0.6129   0.8461
   4.750   1.0802   0.00989   0.00482  -0.1216   0.6048   0.8485
   5.000   1.1049   0.00998   0.00488  -0.1212   0.5970   0.8510
   5.250   1.1285   0.01004   0.00500  -0.1206   0.5879   0.8538
   5.500   1.1526   0.01015   0.00510  -0.1201   0.5789   0.8567
   5.750   1.1755   0.01025   0.00522  -0.1194   0.5689   0.8595
   6.000   1.1966   0.01035   0.00536  -0.1183   0.5583   0.8624
   6.250   1.2171   0.01049   0.00551  -0.1170   0.5470   0.8655
   6.500   1.2366   0.01067   0.00567  -0.1156   0.5346   0.8688
   6.750   1.2552   0.01087   0.00587  -0.1141   0.5204   0.8724
   7.000   1.2705   0.01107   0.00607  -0.1119   0.5055   0.8759
   7.250   1.2832   0.01131   0.00630  -0.1091   0.4900   0.8798
   7.500   1.2950   0.01164   0.00661  -0.1063   0.4724   0.8846
   7.750   1.3079   0.01203   0.00697  -0.1038   0.4545   0.8896
   8.000   1.3169   0.01244   0.00737  -0.1006   0.4351   0.8948
   8.250   1.3258   0.01295   0.00783  -0.0976   0.4156   0.9008
   8.750   1.3391   0.01414   0.00896  -0.0909   0.3761   0.9150
   9.000   1.3445   0.01481   0.00960  -0.0875   0.3566   0.9245
   9.250   1.3475   0.01552   0.01030  -0.0838   0.3379   0.9396
   9.500   1.3541   0.01633   0.01109  -0.0812   0.3184   1.0000
   9.750   1.3646   0.01734   0.01204  -0.0796   0.2976   1.0000
  10.000   1.3735   0.01845   0.01308  -0.0779   0.2778   1.0000
  10.250   1.3812   0.01965   0.01421  -0.0760   0.2592   1.0000
  10.500   1.3877   0.02094   0.01542  -0.0740   0.2410   1.0000
  10.750   1.3949   0.02222   0.01664  -0.0722   0.2228   1.0000
  11.000   1.4013   0.02360   0.01796  -0.0704   0.2050   1.0000
  11.250   1.4074   0.02503   0.01934  -0.0687   0.1889   1.0000
  11.500   1.4137   0.02649   0.02075  -0.0671   0.1741   1.0000
  11.750   1.4196   0.02801   0.02223  -0.0655   0.1599   1.0000
  12.000   1.4254   0.02959   0.02378  -0.0640   0.1465   1.0000
  12.250   1.4309   0.03122   0.02538  -0.0626   0.1339   1.0000
  12.500   1.4360   0.03295   0.02709  -0.0612   0.1220   1.0000
  12.750   1.4406   0.03476   0.02887  -0.0599   0.1101   1.0000
  13.000   1.4448   0.03665   0.03073  -0.0587   0.0996   1.0000
  13.250   1.4487   0.03862   0.03268  -0.0575   0.0892   1.0000
  13.500   1.4531   0.04062   0.03467  -0.0565   0.0796   1.0000
  13.750   1.4574   0.04266   0.03671  -0.0556   0.0711   1.0000
  14.000   1.4603   0.04490   0.03896  -0.0547   0.0636   1.0000
  14.250   1.4618   0.04734   0.04138  -0.0539   0.0566   1.0000
  14.500   1.4662   0.04956   0.04363  -0.0532   0.0506   1.0000
  14.750   1.4682   0.05208   0.04620  -0.0526   0.0458   1.0000
  15.000   1.4692   0.05477   0.04890  -0.0521   0.0410   1.0000
  15.250   1.4720   0.05733   0.05152  -0.0518   0.0372   1.0000
  15.500   1.4710   0.06042   0.05463  -0.0515   0.0337   1.0000
  15.750   1.4738   0.06313   0.05743  -0.0514   0.0309   1.0000
  16.000   1.4726   0.06637   0.06070  -0.0514   0.0282   1.0000
  16.250   1.4746   0.06928   0.06370  -0.0515   0.0257   1.0000
  16.500   1.4737   0.07264   0.06712  -0.0517   0.0239   1.0000
  16.750   1.4716   0.07623   0.07079  -0.0521   0.0220   1.0000
  17.000   1.4717   0.07962   0.07427  -0.0526   0.0203   1.0000
  17.250   1.4672   0.08370   0.07839  -0.0533   0.0187   1.0000
  17.500   1.4672   0.08720   0.08202  -0.0540   0.0175   1.0000
  17.750   1.4650   0.09111   0.08602  -0.0549   0.0163   1.0000
  18.000   1.4577   0.09588   0.09086  -0.0562   0.0153   1.0000
  18.250   1.4561   0.09982   0.09491  -0.0573   0.0143   1.0000
  18.500   1.4534   0.10398   0.09919  -0.0587   0.0133   1.0000
  18.750   1.4462   0.10894   0.10423  -0.0604   0.0126   1.0000
  19.000   1.4380   0.11414   0.10954  -0.0624   0.0119   1.0000
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