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E10(08%) (e228-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 50,000
Max Cl/Cd: 28.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e228-il-50000-n5.txt
Download as CSV file: xf-e228-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E10(08%)                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6959   0.09083   0.08414  -0.0078   1.0000   0.0456
 -10.500  -0.7119   0.08295   0.07626  -0.0134   1.0000   0.0446
 -10.250  -0.7332   0.07559   0.06886  -0.0188   1.0000   0.0437
 -10.000  -0.7563   0.06953   0.06270  -0.0221   1.0000   0.0427
  -9.750  -0.7772   0.06488   0.05789  -0.0228   1.0000   0.0424
  -9.500  -0.7930   0.06079   0.05358  -0.0221   1.0000   0.0426
  -9.250  -0.8021   0.05683   0.04930  -0.0212   1.0000   0.0435
  -9.000  -0.8065   0.05294   0.04501  -0.0200   1.0000   0.0447
  -8.750  -0.8056   0.04914   0.04073  -0.0187   1.0000   0.0460
  -8.500  -0.7990   0.04547   0.03651  -0.0172   1.0000   0.0470
  -8.250  -0.7870   0.04214   0.03261  -0.0157   1.0000   0.0481
  -8.000  -0.7705   0.03925   0.02961  -0.0148   1.0000   0.0501
  -7.750  -0.7523   0.03692   0.02702  -0.0138   1.0000   0.0528
  -7.500  -0.7333   0.03491   0.02466  -0.0127   1.0000   0.0583
  -7.250  -0.7140   0.03298   0.02264  -0.0117   1.0000   0.0639
  -7.000  -0.6928   0.03112   0.02058  -0.0106   1.0000   0.0698
  -6.750  -0.6728   0.02933   0.01870  -0.0093   1.0000   0.0769
  -6.500  -0.6538   0.02774   0.01705  -0.0080   1.0000   0.0890
  -6.250  -0.6355   0.02626   0.01559  -0.0068   1.0000   0.1123
  -6.000  -0.6183   0.02480   0.01437  -0.0055   1.0000   0.1459
  -5.750  -0.6011   0.02355   0.01330  -0.0043   1.0000   0.1960
  -5.500  -0.5837   0.02251   0.01247  -0.0029   1.0000   0.2475
  -5.250  -0.5659   0.02165   0.01177  -0.0014   1.0000   0.2976
  -5.000  -0.5476   0.02092   0.01115   0.0002   1.0000   0.3472
  -4.750  -0.5294   0.02027   0.01063   0.0019   1.0000   0.3949
  -4.500  -0.5108   0.01970   0.01017   0.0037   1.0000   0.4416
  -4.250  -0.4923   0.01921   0.00977   0.0056   1.0000   0.4877
  -4.000  -0.4744   0.01878   0.00939   0.0078   1.0000   0.5325
  -3.750  -0.4562   0.01842   0.00912   0.0100   1.0000   0.5764
  -3.500  -0.4375   0.01812   0.00890   0.0122   1.0000   0.6202
  -3.250  -0.4182   0.01789   0.00874   0.0144   1.0000   0.6635
  -3.000  -0.3977   0.01773   0.00863   0.0165   1.0000   0.7063
  -2.750  -0.3751   0.01764   0.00856   0.0182   1.0000   0.7485
  -2.500  -0.3492   0.01763   0.00850   0.0192   1.0000   0.7895
  -2.250  -0.3191   0.01769   0.00850   0.0194   1.0000   0.8290
  -2.000  -0.2802   0.01783   0.00853   0.0178   1.0000   0.8642
  -1.750  -0.2381   0.01798   0.00852   0.0153   1.0000   0.8963
  -1.500  -0.1895   0.01811   0.00850   0.0113   1.0000   0.9237
  -1.250  -0.1375   0.01818   0.00841   0.0063   1.0000   0.9474
  -1.000  -0.0872   0.01817   0.00830   0.0012   1.0000   0.9712
  -0.750  -0.0341   0.01808   0.00812  -0.0047   1.0000   0.9930
  -0.500  -0.0115   0.01805   0.00803  -0.0057   0.9965   1.0000
  -0.250   0.0355   0.01808   0.00801  -0.0106   0.9770   1.0000
   0.000   0.0847   0.01810   0.00800  -0.0157   0.9595   1.0000
   0.250   0.1334   0.01809   0.00799  -0.0204   0.9420   1.0000
   0.500   0.1741   0.01807   0.00799  -0.0233   0.9207   1.0000
   0.750   0.2135   0.01803   0.00799  -0.0257   0.9001   1.0000
   1.000   0.2438   0.01803   0.00800  -0.0263   0.8764   1.0000
   1.250   0.2714   0.01805   0.00803  -0.0261   0.8532   1.0000
   1.500   0.2962   0.01808   0.00807  -0.0252   0.8304   1.0000
   1.750   0.3176   0.01815   0.00819  -0.0237   0.8062   1.0000
   2.000   0.3388   0.01822   0.00826  -0.0220   0.7827   1.0000
   2.250   0.3596   0.01829   0.00834  -0.0201   0.7595   1.0000
   2.500   0.3795   0.01839   0.00847  -0.0182   0.7346   1.0000
   2.750   0.3997   0.01851   0.00864  -0.0163   0.7099   1.0000
   3.000   0.4201   0.01863   0.00877  -0.0143   0.6849   1.0000
   3.250   0.4406   0.01876   0.00891  -0.0123   0.6590   1.0000
   3.500   0.4611   0.01892   0.00908  -0.0104   0.6319   1.0000
   3.750   0.4815   0.01912   0.00928  -0.0085   0.6034   1.0000
   4.000   0.5019   0.01935   0.00959  -0.0067   0.5731   1.0000
   4.250   0.5223   0.01962   0.00986  -0.0049   0.5412   1.0000
   4.500   0.5429   0.01992   0.01015  -0.0031   0.5079   1.0000
   4.750   0.5632   0.02028   0.01048  -0.0014   0.4726   1.0000
   5.000   0.5830   0.02069   0.01086   0.0003   0.4359   1.0000
   5.250   0.6025   0.02119   0.01132   0.0020   0.3970   1.0000
   5.500   0.6214   0.02177   0.01191   0.0036   0.3569   1.0000
   5.750   0.6397   0.02245   0.01252   0.0052   0.3161   1.0000
   6.000   0.6575   0.02326   0.01323   0.0067   0.2757   1.0000
   6.250   0.6746   0.02420   0.01405   0.0083   0.2368   1.0000
   6.500   0.6914   0.02528   0.01504   0.0097   0.2007   1.0000
   6.750   0.7076   0.02649   0.01613   0.0111   0.1704   1.0000
   7.000   0.7240   0.02781   0.01741   0.0126   0.1442   1.0000
   7.250   0.7404   0.02922   0.01883   0.0140   0.1223   1.0000
   7.500   0.7565   0.03076   0.02044   0.0154   0.1053   1.0000
   7.750   0.7720   0.03233   0.02203   0.0168   0.0908   1.0000
   8.000   0.7891   0.03416   0.02401   0.0183   0.0796   1.0000
   8.250   0.8045   0.03607   0.02608   0.0197   0.0692   1.0000
   8.500   0.8189   0.03808   0.02813   0.0210   0.0617   1.0000
   8.750   0.8340   0.04055   0.03097   0.0224   0.0556   1.0000
   9.000   0.8452   0.04270   0.03313   0.0237   0.0503   1.0000
   9.250   0.8535   0.04554   0.03648   0.0252   0.0460   1.0000
   9.500   0.8600   0.04859   0.03985   0.0267   0.0437   1.0000
   9.750   0.8639   0.05151   0.04299   0.0280   0.0419   1.0000
  10.000   0.8665   0.05437   0.04600   0.0291   0.0402   1.0000
  10.250   0.8574   0.05800   0.04992   0.0306   0.0393   1.0000
  10.500   0.8435   0.06154   0.05372   0.0318   0.0391   1.0000
  10.750   0.8256   0.06576   0.05818   0.0315   0.0389   1.0000
  11.000   0.8091   0.07047   0.06305   0.0299   0.0390   1.0000
  11.250   0.7878   0.07639   0.06914   0.0266   0.0390   1.0000
  11.500   0.7719   0.08254   0.07530   0.0229   0.0395   1.0000
  11.750   0.7543   0.08967   0.08249   0.0183   0.0398   1.0000
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