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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.53 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e433-il-1000000.txt
Download as CSV file: xf-e433-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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  -0.0300   0.08569   0.08392  -0.1164   0.9497   0.0087
 -11.250  -0.0229   0.08012   0.07833  -0.1203   0.9461   0.0087
  -9.750  -0.0828   0.05998   0.05809  -0.1443   0.9333   0.0089
  -9.500  -0.0720   0.04944   0.04736  -0.1567   0.9186   0.0087
  -8.000  -0.1996   0.02298   0.01906  -0.1424   0.8505   0.0067
  -7.750  -0.1878   0.02070   0.01657  -0.1407   0.8461   0.0059
  -7.500  -0.1769   0.01765   0.01300  -0.1386   0.8417   0.0059
  -7.250  -0.1562   0.01646   0.01156  -0.1376   0.8381   0.0062
  -7.000  -0.1340   0.01556   0.01048  -0.1369   0.8345   0.0063
  -6.750  -0.1130   0.01416   0.00886  -0.1361   0.8310   0.0065
  -6.500  -0.0902   0.01318   0.00778  -0.1356   0.8276   0.0069
  -6.250  -0.0659   0.01255   0.00705  -0.1352   0.8243   0.0070
  -6.000  -0.0418   0.01200   0.00646  -0.1348   0.8211   0.0072
  -5.750  -0.0173   0.01149   0.00589  -0.1344   0.8177   0.0074
  -5.500   0.0077   0.01103   0.00537  -0.1341   0.8145   0.0075
  -5.250   0.0335   0.01062   0.00489  -0.1340   0.8112   0.0078
  -5.000   0.0593   0.01030   0.00453  -0.1338   0.8083   0.0081
  -4.750   0.0852   0.00998   0.00419  -0.1336   0.8050   0.0085
  -4.500   0.1110   0.00962   0.00379  -0.1335   0.8017   0.0089
  -4.250   0.1372   0.00923   0.00334  -0.1334   0.7985   0.0094
  -4.000   0.1648   0.00899   0.00305  -0.1335   0.7952   0.0105
  -3.750   0.1912   0.00870   0.00275  -0.1334   0.7921   0.0134
  -3.500   0.2174   0.00829   0.00247  -0.1334   0.7886   0.0423
  -3.250   0.2444   0.00801   0.00231  -0.1335   0.7852   0.0763
  -3.000   0.2718   0.00772   0.00217  -0.1338   0.7817   0.1284
  -2.750   0.2987   0.00727   0.00204  -0.1342   0.7782   0.2313
  -2.500   0.3247   0.00631   0.00184  -0.1349   0.7744   0.4650
  -2.250   0.3522   0.00572   0.00181  -0.1355   0.7707   0.6536
  -2.000   0.3809   0.00573   0.00182  -0.1357   0.7670   0.6842
  -1.750   0.4095   0.00576   0.00183  -0.1359   0.7631   0.7003
  -1.500   0.4374   0.00578   0.00185  -0.1359   0.7589   0.7156
  -1.250   0.4656   0.00581   0.00185  -0.1360   0.7546   0.7250
  -1.000   0.4942   0.00588   0.00186  -0.1363   0.7504   0.7328
  -0.750   0.5221   0.00591   0.00188  -0.1364   0.7462   0.7394
  -0.500   0.5498   0.00595   0.00192  -0.1364   0.7416   0.7463
  -0.250   0.5779   0.00603   0.00195  -0.1365   0.7371   0.7542
   0.000   0.6050   0.00612   0.00206  -0.1363   0.7323   0.7630
   0.250   0.6324   0.00618   0.00211  -0.1362   0.7269   0.7700
   0.500   0.6596   0.00622   0.00214  -0.1362   0.7217   0.7735
   0.750   0.6873   0.00625   0.00216  -0.1363   0.7165   0.7757
   1.000   0.7148   0.00628   0.00217  -0.1363   0.7107   0.7778
   1.250   0.7422   0.00635   0.00218  -0.1364   0.7049   0.7800
   1.500   0.7698   0.00636   0.00221  -0.1365   0.6987   0.7819
   1.750   0.7970   0.00643   0.00223  -0.1365   0.6920   0.7835
   2.000   0.8238   0.00644   0.00225  -0.1365   0.6852   0.7857
   2.250   0.8501   0.00649   0.00228  -0.1363   0.6777   0.7876
   2.500   0.8766   0.00655   0.00234  -0.1362   0.6700   0.7895
   2.750   0.9023   0.00663   0.00240  -0.1359   0.6614   0.7914
   3.000   0.9284   0.00669   0.00246  -0.1357   0.6524   0.7934
   3.250   0.9536   0.00679   0.00253  -0.1354   0.6428   0.7955
   3.500   0.9785   0.00690   0.00260  -0.1349   0.6317   0.7977
   3.750   1.0033   0.00700   0.00269  -0.1345   0.6196   0.7997
   4.000   1.0267   0.00711   0.00278  -0.1338   0.6060   0.8019
   4.250   1.0493   0.00726   0.00290  -0.1329   0.5910   0.8039
   4.500   1.0709   0.00744   0.00304  -0.1318   0.5742   0.8061
   4.750   1.0906   0.00767   0.00320  -0.1303   0.5550   0.8085
   5.000   1.1104   0.00790   0.00337  -0.1289   0.5343   0.8110
   5.250   1.1271   0.00818   0.00357  -0.1268   0.5117   0.8135
   5.500   1.1423   0.00846   0.00377  -0.1245   0.4896   0.8162
   5.750   1.1572   0.00877   0.00402  -0.1221   0.4672   0.8190
   6.000   1.1721   0.00914   0.00430  -0.1198   0.4443   0.8217
   6.250   1.1870   0.00952   0.00461  -0.1175   0.4216   0.8246
   6.500   1.2014   0.00994   0.00494  -0.1152   0.3982   0.8276
   6.750   1.2161   0.01038   0.00528  -0.1130   0.3756   0.8303
   7.000   1.2295   0.01083   0.00566  -0.1106   0.3521   0.8335
   7.250   1.2436   0.01129   0.00606  -0.1084   0.3306   0.8368
   7.500   1.2570   0.01179   0.00649  -0.1061   0.3102   0.8405
   7.750   1.2709   0.01232   0.00693  -0.1040   0.2888   0.8440
   8.000   1.2838   0.01286   0.00742  -0.1017   0.2689   0.8476
   8.250   1.2962   0.01344   0.00794  -0.0994   0.2494   0.8515
   8.500   1.3082   0.01409   0.00851  -0.0972   0.2278   0.8556
   9.000   1.3312   0.01548   0.00976  -0.0927   0.1896   0.8644
   9.250   1.3428   0.01619   0.01043  -0.0905   0.1721   0.8697
   9.500   1.3533   0.01702   0.01118  -0.0883   0.1539   0.8752
   9.750   1.3621   0.01790   0.01199  -0.0859   0.1349   0.8813
  10.000   1.3739   0.01867   0.01275  -0.0840   0.1231   0.8883
  10.250   1.3809   0.01971   0.01370  -0.0815   0.1027   0.8965
  10.500   1.3904   0.02062   0.01459  -0.0794   0.0899   0.9071
  10.750   1.3981   0.02151   0.01550  -0.0769   0.0784   0.9251
  11.000   1.4075   0.02235   0.01639  -0.0749   0.0687   1.0000
  11.250   1.4189   0.02340   0.01740  -0.0735   0.0599   1.0000
  11.500   1.4287   0.02457   0.01853  -0.0719   0.0509   1.0000
  11.750   1.4402   0.02564   0.01959  -0.0706   0.0449   1.0000
  12.000   1.4501   0.02684   0.02077  -0.0691   0.0383   1.0000
  12.250   1.4598   0.02808   0.02200  -0.0677   0.0330   1.0000
  12.500   1.4690   0.02938   0.02330  -0.0663   0.0284   1.0000
  12.750   1.4793   0.03063   0.02457  -0.0651   0.0250   1.0000
  13.000   1.4876   0.03206   0.02601  -0.0637   0.0213   1.0000
  13.250   1.4966   0.03346   0.02743  -0.0625   0.0188   1.0000
  13.500   1.5053   0.03493   0.02893  -0.0614   0.0166   1.0000
  13.750   1.5139   0.03643   0.03047  -0.0603   0.0149   1.0000
  14.000   1.5213   0.03809   0.03216  -0.0592   0.0132   1.0000
  14.250   1.5300   0.03966   0.03378  -0.0583   0.0119   1.0000
  14.500   1.5362   0.04150   0.03566  -0.0573   0.0107   1.0000
  14.750   1.5437   0.04325   0.03747  -0.0565   0.0096   1.0000
  15.000   1.5501   0.04517   0.03944  -0.0557   0.0086   1.0000
  15.250   1.5550   0.04727   0.04160  -0.0550   0.0076   1.0000
  15.500   1.5612   0.04930   0.04370  -0.0544   0.0068   1.0000
  15.750   1.5643   0.05170   0.04614  -0.0538   0.0056   1.0000
  16.000   1.5676   0.05415   0.04865  -0.0533   0.0045   1.0000
  16.250   1.5677   0.05703   0.05159  -0.0529   0.0033   1.0000
  16.500   1.5605   0.06089   0.05552  -0.0525   0.0017   1.0000
  16.750   1.5590   0.06418   0.05891  -0.0523   0.0013   1.0000
  17.000   1.5521   0.06827   0.06311  -0.0524   0.0009   1.0000
  17.250   1.5518   0.07160   0.06655  -0.0527   0.0009   1.0000
  17.500   1.5497   0.07528   0.07034  -0.0531   0.0008   1.0000
  17.750   1.5470   0.07911   0.07428  -0.0538   0.0007   1.0000
  18.000   1.5428   0.08325   0.07854  -0.0546   0.0007   1.0000
  18.250   1.5385   0.08753   0.08293  -0.0556   0.0006   1.0000
  18.500   1.5325   0.09217   0.08768  -0.0569   0.0006   1.0000
  18.750   1.5252   0.09711   0.09274  -0.0585   0.0006   1.0000
  19.000   1.5162   0.10242   0.09818  -0.0603   0.0005   1.0000
  19.250   1.5083   0.10765   0.10353  -0.0623   0.0005   1.0000
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