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E10(08%) (e228-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 100,000
Max Cl/Cd: 38.67 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e228-il-100000-n5.txt
Download as CSV file: xf-e228-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7545   0.07959   0.07479  -0.0102   1.0000   0.0205
 -11.000  -0.7940   0.06788   0.06285  -0.0200   1.0000   0.0196
 -10.750  -0.8193   0.06146   0.05621  -0.0241   1.0000   0.0194
 -10.500  -0.8391   0.05695   0.05152  -0.0251   1.0000   0.0193
 -10.250  -0.8553   0.05333   0.04763  -0.0240   1.0000   0.0193
 -10.000  -0.8661   0.05019   0.04424  -0.0221   1.0000   0.0195
  -9.750  -0.8700   0.04704   0.04081  -0.0205   1.0000   0.0198
  -9.500  -0.8690   0.04409   0.03756  -0.0189   1.0000   0.0203
  -9.250  -0.8626   0.04168   0.03488  -0.0175   1.0000   0.0214
  -9.000  -0.8532   0.03939   0.03228  -0.0161   1.0000   0.0229
  -8.750  -0.8419   0.03691   0.02939  -0.0146   1.0000   0.0244
  -8.500  -0.8276   0.03441   0.02647  -0.0132   1.0000   0.0255
  -8.250  -0.8104   0.03213   0.02385  -0.0119   1.0000   0.0263
  -8.000  -0.7940   0.02952   0.02108  -0.0107   1.0000   0.0278
  -7.750  -0.7755   0.02817   0.01965  -0.0098   1.0000   0.0304
  -7.500  -0.7554   0.02682   0.01812  -0.0088   1.0000   0.0335
  -7.250  -0.7350   0.02532   0.01638  -0.0076   1.0000   0.0354
  -7.000  -0.7160   0.02386   0.01480  -0.0062   1.0000   0.0374
  -6.750  -0.6979   0.02257   0.01347  -0.0049   1.0000   0.0405
  -6.500  -0.6780   0.02159   0.01238  -0.0037   1.0000   0.0455
  -6.250  -0.6590   0.02053   0.01130  -0.0024   1.0000   0.0532
  -6.000  -0.6400   0.01949   0.01024  -0.0010   1.0000   0.0637
  -5.750  -0.6211   0.01848   0.00929   0.0004   1.0000   0.0845
  -5.500  -0.6019   0.01762   0.00852   0.0016   1.0000   0.1152
  -5.250  -0.5830   0.01685   0.00796   0.0029   1.0000   0.1577
  -5.000  -0.5653   0.01610   0.00752   0.0043   1.0000   0.2133
  -4.750  -0.5474   0.01551   0.00713   0.0059   1.0000   0.2640
  -4.500  -0.5293   0.01502   0.00677   0.0075   1.0000   0.3039
  -4.250  -0.5113   0.01459   0.00646   0.0091   1.0000   0.3433
  -4.000  -0.4937   0.01421   0.00619   0.0109   1.0000   0.3839
  -3.750  -0.4761   0.01387   0.00593   0.0127   1.0000   0.4236
  -3.500  -0.4587   0.01357   0.00574   0.0145   1.0000   0.4640
  -3.250  -0.4280   0.01329   0.00559   0.0137   0.9929   0.5117
  -3.000  -0.3917   0.01305   0.00547   0.0119   0.9836   0.5616
  -2.750  -0.3559   0.01284   0.00535   0.0104   0.9742   0.6090
  -2.500  -0.3183   0.01269   0.00530   0.0086   0.9657   0.6555
  -2.250  -0.2806   0.01257   0.00526   0.0069   0.9569   0.6993
  -2.000  -0.2447   0.01249   0.00525   0.0057   0.9466   0.7390
  -1.750  -0.2076   0.01245   0.00523   0.0044   0.9365   0.7755
  -1.500  -0.1688   0.01245   0.00524   0.0028   0.9267   0.8077
  -1.250  -0.1311   0.01247   0.00525   0.0014   0.9152   0.8355
  -1.000  -0.0936   0.01250   0.00526   0.0000   0.9027   0.8596
  -0.750  -0.0555   0.01254   0.00527  -0.0015   0.8895   0.8803
  -0.500  -0.0192   0.01258   0.00526  -0.0027   0.8752   0.8996
  -0.250   0.0189   0.01262   0.00526  -0.0042   0.8603   0.9153
   0.000   0.0563   0.01265   0.00524  -0.0056   0.8447   0.9299
   0.250   0.0939   0.01268   0.00522  -0.0072   0.8278   0.9430
   0.500   0.1309   0.01269   0.00520  -0.0087   0.8094   0.9557
   0.750   0.1692   0.01268   0.00514  -0.0106   0.7903   0.9671
   1.000   0.2077   0.01265   0.00508  -0.0125   0.7701   0.9779
   1.250   0.2461   0.01260   0.00499  -0.0146   0.7480   0.9884
   1.500   0.2852   0.01254   0.00490  -0.0169   0.7247   0.9985
   1.750   0.3088   0.01254   0.00485  -0.0160   0.7024   1.0000
   2.000   0.3299   0.01257   0.00484  -0.0147   0.6787   1.0000
   2.250   0.3511   0.01263   0.00485  -0.0134   0.6551   1.0000
   2.500   0.3725   0.01272   0.00487  -0.0120   0.6310   1.0000
   2.750   0.3942   0.01283   0.00496  -0.0108   0.6055   1.0000
   3.000   0.4161   0.01297   0.00505  -0.0095   0.5787   1.0000
   3.250   0.4380   0.01314   0.00517  -0.0083   0.5509   1.0000
   3.500   0.4600   0.01334   0.00530  -0.0071   0.5219   1.0000
   3.750   0.4819   0.01357   0.00547  -0.0059   0.4915   1.0000
   4.000   0.5039   0.01383   0.00571  -0.0048   0.4595   1.0000
   4.250   0.5258   0.01413   0.00594  -0.0036   0.4264   1.0000
   4.750   0.5690   0.01487   0.00652  -0.0014   0.3570   1.0000
   5.000   0.5903   0.01531   0.00688  -0.0003   0.3211   1.0000
   5.250   0.6113   0.01581   0.00728   0.0008   0.2832   1.0000
   5.500   0.6321   0.01636   0.00779   0.0018   0.2459   1.0000
   5.750   0.6523   0.01700   0.00831   0.0029   0.2094   1.0000
   6.000   0.6724   0.01769   0.00890   0.0040   0.1748   1.0000
   6.250   0.6919   0.01845   0.00956   0.0052   0.1450   1.0000
   6.500   0.7112   0.01926   0.01031   0.0064   0.1192   1.0000
   6.750   0.7300   0.02015   0.01115   0.0076   0.0990   1.0000
   7.000   0.7485   0.02108   0.01208   0.0089   0.0814   1.0000
   7.250   0.7663   0.02211   0.01318   0.0103   0.0685   1.0000
   7.500   0.7837   0.02318   0.01428   0.0117   0.0565   1.0000
   7.750   0.8001   0.02437   0.01551   0.0131   0.0474   1.0000
   8.000   0.8156   0.02562   0.01675   0.0145   0.0393   1.0000
   8.250   0.8322   0.02684   0.01816   0.0160   0.0329   1.0000
   8.500   0.8452   0.02840   0.01974   0.0176   0.0284   1.0000
   8.750   0.8603   0.02997   0.02155   0.0193   0.0256   1.0000
   9.000   0.8740   0.03170   0.02346   0.0209   0.0234   1.0000
   9.250   0.8865   0.03349   0.02544   0.0224   0.0220   1.0000
   9.500   0.8969   0.03558   0.02765   0.0240   0.0209   1.0000
   9.750   0.9049   0.03819   0.03048   0.0257   0.0199   1.0000
  10.000   0.9121   0.04051   0.03314   0.0274   0.0190   1.0000
  10.250   0.9153   0.04276   0.03571   0.0292   0.0177   1.0000
  10.500   0.9135   0.04514   0.03835   0.0313   0.0171   1.0000
  10.750   0.9074   0.04762   0.04105   0.0332   0.0165   1.0000
  11.000   0.8990   0.05063   0.04429   0.0343   0.0163   1.0000
  11.250   0.8877   0.05412   0.04799   0.0343   0.0160   1.0000
  11.500   0.8741   0.05832   0.05242   0.0332   0.0159   1.0000
  11.750   0.8564   0.06365   0.05797   0.0307   0.0161   1.0000
  12.000   0.8367   0.07003   0.06456   0.0267   0.0163   1.0000
  12.250   0.8129   0.07810   0.07281   0.0210   0.0164   1.0000
  12.500   0.7772   0.09026   0.08515   0.0125   0.0176   1.0000
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