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E392 (10.15%) (e392-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E392 (10.15%) (e392-il)
Reynolds number: 200,000
Max Cl/Cd: 84.62 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e392-il-200000-n5.txt
Download as CSV file: xf-e392-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E392  (10.15%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3303   0.08985   0.08642  -0.0409   1.0000   0.0162
  -8.500  -0.3270   0.08762   0.08423  -0.0404   1.0000   0.0156
  -8.250  -0.3279   0.08469   0.08136  -0.0406   1.0000   0.0151
  -8.000  -0.3317   0.08169   0.07844  -0.0408   1.0000   0.0146
  -7.750  -0.3341   0.07818   0.07501  -0.0421   0.9964   0.0142
  -7.500  -0.3225   0.07195   0.06878  -0.0499   0.9785   0.0134
  -7.250  -0.3070   0.05729   0.05408  -0.0703   0.9548   0.0118
  -7.000  -0.2866   0.04841   0.04499  -0.0818   0.9356   0.0116
  -6.750  -0.2675   0.03952   0.03567  -0.0904   0.9172   0.0114
  -6.250  -0.2254   0.02734   0.02204  -0.0975   0.8840   0.0120
  -6.000  -0.2007   0.02541   0.01982  -0.0985   0.8691   0.0128
  -5.750  -0.1755   0.02332   0.01732  -0.0990   0.8548   0.0134
  -5.500  -0.1501   0.02096   0.01443  -0.0990   0.8413   0.0134
  -5.250  -0.1243   0.01921   0.01227  -0.0988   0.8283   0.0137
  -5.000  -0.0983   0.01783   0.01058  -0.0985   0.8159   0.0141
  -4.750  -0.0720   0.01670   0.00920  -0.0982   0.8042   0.0145
  -4.500  -0.0457   0.01575   0.00803  -0.0979   0.7933   0.0152
  -4.000   0.0074   0.01430   0.00628  -0.0975   0.7726   0.0177
  -3.750   0.0344   0.01387   0.00574  -0.0974   0.7632   0.0207
  -3.500   0.0615   0.01333   0.00505  -0.0972   0.7544   0.0234
  -3.250   0.0889   0.01286   0.00449  -0.0971   0.7454   0.0302
  -3.000   0.1163   0.01241   0.00405  -0.0971   0.7374   0.0530
  -2.750   0.1434   0.01200   0.00378  -0.0972   0.7291   0.0968
  -2.500   0.1705   0.01157   0.00356  -0.0973   0.7217   0.1649
  -2.250   0.1977   0.01123   0.00337  -0.0974   0.7141   0.2334
  -2.000   0.2248   0.01088   0.00324  -0.0975   0.7073   0.3195
  -1.750   0.2515   0.01056   0.00317  -0.0974   0.7001   0.4188
  -1.500   0.2781   0.01034   0.00313  -0.0972   0.6939   0.5077
  -1.250   0.3046   0.01017   0.00312  -0.0969   0.6869   0.5776
  -1.000   0.3306   0.01006   0.00309  -0.0963   0.6811   0.6377
  -0.750   0.3561   0.00993   0.00310  -0.0957   0.6745   0.6956
  -0.500   0.3806   0.00983   0.00310  -0.0946   0.6686   0.7538
  -0.250   0.4036   0.00973   0.00310  -0.0932   0.6629   0.8141
   0.000   0.4268   0.00962   0.00306  -0.0917   0.6568   0.8834
   0.250   0.4641   0.00952   0.00293  -0.0934   0.6515   0.9897
   0.500   0.4925   0.00961   0.00294  -0.0936   0.6452   1.0000
   0.750   0.5204   0.00972   0.00295  -0.0937   0.6396   1.0000
   1.000   0.5483   0.00983   0.00299  -0.0938   0.6342   1.0000
   1.250   0.5761   0.00994   0.00304  -0.0938   0.6281   1.0000
   1.500   0.6039   0.01007   0.00309  -0.0939   0.6230   1.0000
   1.750   0.6317   0.01019   0.00319  -0.0939   0.6170   1.0000
   2.000   0.6593   0.01031   0.00328  -0.0939   0.6113   1.0000
   2.250   0.6870   0.01045   0.00337  -0.0939   0.6061   1.0000
   2.500   0.7145   0.01058   0.00352  -0.0939   0.5997   1.0000
   2.750   0.7421   0.01072   0.00362  -0.0939   0.5942   1.0000
   3.000   0.7694   0.01086   0.00377  -0.0939   0.5877   1.0000
   3.250   0.7967   0.01099   0.00391  -0.0938   0.5811   1.0000
   3.500   0.8238   0.01113   0.00408  -0.0937   0.5736   1.0000
   3.750   0.8507   0.01127   0.00421  -0.0936   0.5656   1.0000
   4.000   0.8775   0.01141   0.00439  -0.0934   0.5567   1.0000
   4.250   0.9042   0.01156   0.00456  -0.0932   0.5481   1.0000
   4.500   0.9307   0.01170   0.00474  -0.0930   0.5381   1.0000
   4.750   0.9570   0.01185   0.00494  -0.0927   0.5274   1.0000
   5.000   0.9830   0.01201   0.00513  -0.0924   0.5161   1.0000
   5.250   1.0088   0.01219   0.00536  -0.0921   0.5038   1.0000
   5.500   1.0343   0.01237   0.00558  -0.0917   0.4902   1.0000
   5.750   1.0594   0.01258   0.00583  -0.0912   0.4744   1.0000
   6.000   1.0840   0.01281   0.00609  -0.0907   0.4553   1.0000
   6.250   1.1070   0.01312   0.00638  -0.0899   0.4269   1.0000
   6.500   1.1276   0.01359   0.00671  -0.0887   0.3837   1.0000
   6.750   1.1439   0.01441   0.00720  -0.0870   0.3204   1.0000
   7.000   1.1583   0.01546   0.00792  -0.0853   0.2584   1.0000
   7.250   1.1730   0.01652   0.00873  -0.0836   0.2091   1.0000
   7.500   1.1868   0.01765   0.00963  -0.0819   0.1613   1.0000
   7.750   1.1996   0.01882   0.01055  -0.0801   0.1196   1.0000
   8.000   1.2124   0.01994   0.01149  -0.0782   0.0871   1.0000
   8.250   1.2256   0.02098   0.01242  -0.0764   0.0643   1.0000
   8.500   1.2368   0.02209   0.01345  -0.0743   0.0441   1.0000
   8.750   1.2456   0.02321   0.01454  -0.0718   0.0311   1.0000
   9.000   1.2534   0.02435   0.01568  -0.0692   0.0248   1.0000
   9.250   1.2628   0.02542   0.01688  -0.0670   0.0219   1.0000
   9.500   1.2701   0.02667   0.01819  -0.0647   0.0199   1.0000
   9.750   1.2764   0.02806   0.01967  -0.0625   0.0185   1.0000
  10.000   1.2840   0.02940   0.02114  -0.0607   0.0174   1.0000
  10.250   1.2906   0.03089   0.02275  -0.0590   0.0165   1.0000
  10.500   1.2962   0.03256   0.02454  -0.0574   0.0158   1.0000
  10.750   1.3006   0.03441   0.02651  -0.0559   0.0153   1.0000
  11.000   1.3040   0.03645   0.02866  -0.0546   0.0149   1.0000
  11.250   1.3058   0.03873   0.03107  -0.0535   0.0145   1.0000
  11.500   1.3056   0.04132   0.03377  -0.0524   0.0141   1.0000
  11.750   1.3062   0.04393   0.03648  -0.0515   0.0138   1.0000
  12.000   1.3097   0.04632   0.03901  -0.0507   0.0136   1.0000
  12.250   1.3134   0.04878   0.04160  -0.0500   0.0134   1.0000
  12.500   1.3171   0.05127   0.04423  -0.0494   0.0132   1.0000
  12.750   1.3211   0.05381   0.04693  -0.0489   0.0128   1.0000
  13.000   1.3246   0.05645   0.04971  -0.0485   0.0124   1.0000
  13.250   1.3275   0.05921   0.05263  -0.0482   0.0120   1.0000
  13.500   1.3296   0.06212   0.05569  -0.0481   0.0116   1.0000
  13.750   1.3310   0.06520   0.05895  -0.0481   0.0114   1.0000
  14.000   1.3316   0.06846   0.06237  -0.0482   0.0111   1.0000
  14.250   1.3314   0.07194   0.06601  -0.0484   0.0109   1.0000
  14.500   1.3300   0.07566   0.06989  -0.0489   0.0108   1.0000
  14.750   1.3272   0.07965   0.07405  -0.0497   0.0106   1.0000
  15.000   1.3235   0.08393   0.07851  -0.0507   0.0105   1.0000
  15.250   1.3183   0.08855   0.08331  -0.0519   0.0103   1.0000
  15.500   1.3117   0.09353   0.08847  -0.0536   0.0102   1.0000
  15.750   1.3035   0.09893   0.09405  -0.0556   0.0101   1.0000
  16.000   1.2938   0.10477   0.10010  -0.0580   0.0101   1.0000
  16.250   1.2828   0.11108   0.10660  -0.0610   0.0100   1.0000
  16.500   1.2699   0.11796   0.11368  -0.0645   0.0099   1.0000
  16.750   1.2562   0.12534   0.12127  -0.0686   0.0098   1.0000
  17.000   1.2422   0.13314   0.12926  -0.0733   0.0098   1.0000
  17.250   1.2281   0.14137   0.13768  -0.0786   0.0098   1.0000
  17.500   1.2138   0.15014   0.14663  -0.0844   0.0098   1.0000
  17.750   1.1989   0.15962   0.15630  -0.0908   0.0099   1.0000
  18.000   1.1764   0.17261   0.16953  -0.0996   0.0101   1.0000
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