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E230 (9.96%) (e230-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E230 (9.96%) (e230-il)
Reynolds number: 50,000
Max Cl/Cd: 24.41 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e230-il-50000-n5.txt
Download as CSV file: xf-e230-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E230  (9.96%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8073   0.09595   0.08925   0.0117   1.0000   0.0353
 -11.250  -0.8243   0.08820   0.08143   0.0063   1.0000   0.0350
 -11.000  -0.8422   0.08139   0.07454   0.0017   1.0000   0.0347
 -10.750  -0.8619   0.07535   0.06836  -0.0018   1.0000   0.0345
 -10.500  -0.8800   0.07039   0.06321  -0.0035   1.0000   0.0344
 -10.250  -0.8973   0.06602   0.05863  -0.0036   1.0000   0.0343
 -10.000  -0.9111   0.06219   0.05455  -0.0023   1.0000   0.0343
  -9.750  -0.9201   0.05843   0.05046  -0.0008   1.0000   0.0344
  -9.500  -0.9228   0.05472   0.04636   0.0007   1.0000   0.0345
  -9.250  -0.9205   0.05108   0.04228   0.0023   1.0000   0.0349
  -9.000  -0.9128   0.04776   0.03847   0.0038   1.0000   0.0355
  -8.750  -0.9010   0.04485   0.03544   0.0048   1.0000   0.0370
  -8.500  -0.8871   0.04250   0.03290   0.0059   1.0000   0.0391
  -8.250  -0.8705   0.04010   0.03016   0.0070   1.0000   0.0418
  -8.000  -0.8505   0.03768   0.02735   0.0080   1.0000   0.0445
  -7.750  -0.8307   0.03539   0.02491   0.0091   1.0000   0.0472
  -7.500  -0.8125   0.03345   0.02288   0.0103   1.0000   0.0512
  -7.250  -0.7941   0.03157   0.02084   0.0116   1.0000   0.0585
  -7.000  -0.7773   0.02974   0.01901   0.0129   1.0000   0.0714
  -6.750  -0.7609   0.02785   0.01721   0.0143   1.0000   0.0968
  -6.500  -0.7451   0.02620   0.01588   0.0153   1.0000   0.1475
  -6.250  -0.7288   0.02478   0.01475   0.0166   1.0000   0.1996
  -6.000  -0.7104   0.02369   0.01377   0.0179   1.0000   0.2492
  -5.750  -0.6917   0.02275   0.01296   0.0192   1.0000   0.2961
  -5.500  -0.6720   0.02194   0.01224   0.0205   1.0000   0.3418
  -5.250  -0.6517   0.02121   0.01156   0.0219   1.0000   0.3866
  -5.000  -0.6309   0.02056   0.01098   0.0233   1.0000   0.4315
  -4.750  -0.6095   0.01998   0.01048   0.0247   1.0000   0.4762
  -4.500  -0.5875   0.01947   0.01005   0.0261   1.0000   0.5207
  -4.250  -0.5647   0.01903   0.00965   0.0274   1.0000   0.5647
  -4.000  -0.5409   0.01866   0.00934   0.0288   1.0000   0.6078
  -3.750  -0.5163   0.01838   0.00910   0.0300   1.0000   0.6502
  -3.500  -0.4892   0.01820   0.00892   0.0310   1.0000   0.6908
  -3.250  -0.4595   0.01810   0.00882   0.0315   1.0000   0.7291
  -3.000  -0.4276   0.01808   0.00875   0.0316   1.0000   0.7650
  -2.750  -0.3943   0.01811   0.00870   0.0313   1.0000   0.7979
  -2.500  -0.3571   0.01821   0.00867   0.0302   1.0000   0.8266
  -2.250  -0.3166   0.01833   0.00868   0.0284   1.0000   0.8515
  -2.000  -0.2775   0.01841   0.00864   0.0266   1.0000   0.8751
  -1.750  -0.2321   0.01850   0.00861   0.0235   1.0000   0.8948
  -1.500  -0.1903   0.01853   0.00855   0.0208   1.0000   0.9150
  -1.250  -0.1465   0.01850   0.00845   0.0174   1.0000   0.9334
  -1.000  -0.1013   0.01840   0.00832   0.0135   1.0000   0.9507
  -0.750  -0.0570   0.01825   0.00816   0.0096   1.0000   0.9679
  -0.500  -0.0118   0.01806   0.00799   0.0052   1.0000   0.9844
  -0.250   0.0373   0.01773   0.00771  -0.0001   1.0000   0.9987
   0.000   0.0475   0.01776   0.00781   0.0012   0.9988   1.0000
   0.250   0.0944   0.01780   0.00788  -0.0037   0.9616   1.0000
   0.500   0.1402   0.01779   0.00791  -0.0078   0.9303   1.0000
   0.750   0.1744   0.01781   0.00798  -0.0093   0.8971   1.0000
   1.000   0.1995   0.01786   0.00804  -0.0088   0.8653   1.0000
   1.250   0.2197   0.01792   0.00810  -0.0071   0.8352   1.0000
   1.500   0.2382   0.01798   0.00818  -0.0051   0.8062   1.0000
   1.750   0.2562   0.01804   0.00825  -0.0028   0.7782   1.0000
   2.000   0.2741   0.01812   0.00832  -0.0005   0.7508   1.0000
   2.250   0.2923   0.01820   0.00840   0.0018   0.7234   1.0000
   2.500   0.3112   0.01830   0.00853   0.0039   0.6948   1.0000
   2.750   0.3305   0.01841   0.00866   0.0060   0.6656   1.0000
   3.000   0.3501   0.01854   0.00879   0.0080   0.6354   1.0000
   3.250   0.3701   0.01870   0.00894   0.0099   0.6042   1.0000
   3.500   0.3905   0.01889   0.00916   0.0117   0.5707   1.0000
   3.750   0.4111   0.01912   0.00939   0.0134   0.5356   1.0000
   4.000   0.4316   0.01939   0.00962   0.0151   0.4996   1.0000
   4.250   0.4525   0.01972   0.00995   0.0166   0.4600   1.0000
   4.500   0.4731   0.02012   0.01033   0.0181   0.4192   1.0000
   4.750   0.4938   0.02060   0.01076   0.0195   0.3767   1.0000
   5.000   0.5144   0.02119   0.01128   0.0207   0.3322   1.0000
   5.250   0.5346   0.02190   0.01190   0.0218   0.2866   1.0000
   5.500   0.5541   0.02275   0.01266   0.0229   0.2413   1.0000
   5.750   0.5730   0.02379   0.01360   0.0240   0.1977   1.0000
   6.000   0.5908   0.02506   0.01471   0.0250   0.1549   1.0000
   6.250   0.6074   0.02643   0.01584   0.0259   0.1119   1.0000
   6.500   0.6237   0.02800   0.01730   0.0271   0.0849   1.0000
   6.750   0.6398   0.02962   0.01890   0.0285   0.0696   1.0000
   7.000   0.6566   0.03130   0.02070   0.0300   0.0610   1.0000
   7.250   0.6731   0.03302   0.02248   0.0315   0.0562   1.0000
   7.500   0.6910   0.03503   0.02469   0.0331   0.0528   1.0000
   7.750   0.7083   0.03710   0.02707   0.0345   0.0494   1.0000
   8.000   0.7234   0.03905   0.02920   0.0357   0.0462   1.0000
   8.250   0.7370   0.04128   0.03143   0.0369   0.0439   1.0000
   8.500   0.7480   0.04415   0.03481   0.0383   0.0426   1.0000
   8.750   0.7554   0.04736   0.03845   0.0396   0.0418   1.0000
   9.000   0.7581   0.05083   0.04235   0.0409   0.0414   1.0000
   9.250   0.7548   0.05459   0.04647   0.0419   0.0410   1.0000
   9.500   0.7464   0.05846   0.05063   0.0427   0.0409   1.0000
   9.750   0.7321   0.06244   0.05482   0.0431   0.0410   1.0000
  10.000   0.7120   0.06661   0.05911   0.0427   0.0412   1.0000
  10.250   0.6907   0.07197   0.06453   0.0400   0.0415   1.0000
  10.500   0.6702   0.07855   0.07117   0.0355   0.0419   1.0000
  10.750   0.6522   0.08600   0.07863   0.0304   0.0424   1.0000
  11.000   0.6384   0.09344   0.08605   0.0259   0.0429   1.0000
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