Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E10(08%) (e228-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E10(08%) (e228-il)
Reynolds number: 200,000
Max Cl/Cd: 51.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e228-il-200000.txt
Download as CSV file: xf-e228-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6712   0.09316   0.08987  -0.0011   1.0000   0.0653
 -10.000  -0.7206   0.05403   0.05061  -0.0251   1.0000   0.0361
  -9.750  -0.7447   0.04931   0.04576  -0.0255   1.0000   0.0354
  -9.500  -0.8599   0.05000   0.04534  -0.0192   1.0000   0.0286
  -9.250  -0.8647   0.04537   0.04039  -0.0175   1.0000   0.0290
  -9.000  -0.8612   0.04181   0.03644  -0.0156   1.0000   0.0289
  -8.750  -0.8503   0.03927   0.03355  -0.0138   1.0000   0.0284
  -8.500  -0.8370   0.03672   0.03067  -0.0122   1.0000   0.0282
  -8.250  -0.8242   0.03344   0.02700  -0.0106   1.0000   0.0281
  -8.000  -0.8111   0.02931   0.02240  -0.0089   1.0000   0.0285
  -7.750  -0.7932   0.02595   0.01875  -0.0077   1.0000   0.0294
  -7.500  -0.7727   0.02427   0.01700  -0.0069   1.0000   0.0315
  -7.250  -0.7508   0.02304   0.01565  -0.0060   1.0000   0.0342
  -7.000  -0.7281   0.02155   0.01398  -0.0049   1.0000   0.0360
  -6.750  -0.7051   0.02038   0.01265  -0.0039   1.0000   0.0377
  -6.500  -0.6865   0.01853   0.01083  -0.0025   1.0000   0.0416
  -6.250  -0.6654   0.01761   0.00987  -0.0014   1.0000   0.0458
  -6.000  -0.6454   0.01662   0.00879   0.0001   1.0000   0.0500
  -5.750  -0.6275   0.01558   0.00778   0.0018   1.0000   0.0589
  -5.500  -0.6118   0.01441   0.00678   0.0039   1.0000   0.0833
  -5.250  -0.5977   0.01326   0.00603   0.0061   1.0000   0.1473
  -5.000  -0.5807   0.01266   0.00562   0.0079   1.0000   0.1955
  -4.750  -0.5640   0.01216   0.00529   0.0097   1.0000   0.2413
  -4.500  -0.5478   0.01172   0.00503   0.0116   1.0000   0.2867
  -4.250  -0.5319   0.01133   0.00484   0.0135   1.0000   0.3375
  -4.000  -0.5163   0.01097   0.00468   0.0155   1.0000   0.3878
  -3.750  -0.5001   0.01068   0.00456   0.0175   1.0000   0.4355
  -3.500  -0.4834   0.01045   0.00446   0.0193   1.0000   0.4791
  -3.250  -0.4490   0.01021   0.00440   0.0176   0.9946   0.5340
  -3.000  -0.4098   0.00996   0.00435   0.0151   0.9866   0.5913
  -2.750  -0.3704   0.00977   0.00432   0.0128   0.9791   0.6446
  -2.500  -0.3299   0.00960   0.00429   0.0104   0.9719   0.6944
  -2.250  -0.2909   0.00947   0.00428   0.0084   0.9641   0.7391
  -2.000  -0.2485   0.00937   0.00427   0.0059   0.9579   0.7797
  -1.750  -0.2115   0.00932   0.00429   0.0046   0.9487   0.8149
  -1.500  -0.1711   0.00930   0.00432   0.0027   0.9413   0.8454
  -1.250  -0.1358   0.00933   0.00435   0.0020   0.9305   0.8720
  -1.000  -0.0996   0.00940   0.00441   0.0011   0.9191   0.8934
  -0.750  -0.0650   0.00948   0.00446   0.0006   0.9069   0.9125
  -0.500  -0.0286   0.00957   0.00451  -0.0004   0.8944   0.9273
  -0.250   0.0128   0.00967   0.00456  -0.0024   0.8815   0.9375
   0.000   0.0545   0.00974   0.00458  -0.0046   0.8670   0.9470
   0.250   0.0936   0.00980   0.00458  -0.0064   0.8507   0.9579
   0.500   0.1334   0.00983   0.00456  -0.0084   0.8334   0.9685
   0.750   0.1769   0.00981   0.00447  -0.0113   0.8152   0.9770
   1.000   0.2191   0.00976   0.00437  -0.0141   0.7947   0.9865
   1.250   0.2620   0.00966   0.00421  -0.0171   0.7730   0.9953
   1.500   0.2957   0.00954   0.00403  -0.0184   0.7498   1.0000
   1.750   0.3154   0.00951   0.00393  -0.0169   0.7281   1.0000
   2.000   0.3360   0.00950   0.00386  -0.0155   0.7042   1.0000
   2.250   0.3570   0.00952   0.00380  -0.0142   0.6805   1.0000
   2.500   0.3784   0.00956   0.00375  -0.0129   0.6560   1.0000
   2.750   0.4003   0.00962   0.00376  -0.0117   0.6293   1.0000
   3.000   0.4224   0.00971   0.00378  -0.0106   0.6020   1.0000
   3.250   0.4447   0.00984   0.00383  -0.0095   0.5738   1.0000
   3.500   0.4670   0.00999   0.00390  -0.0083   0.5442   1.0000
   3.750   0.4894   0.01018   0.00402  -0.0073   0.5137   1.0000
   4.000   0.5118   0.01039   0.00415  -0.0062   0.4814   1.0000
   4.250   0.5342   0.01063   0.00432  -0.0052   0.4473   1.0000
   4.500   0.5563   0.01093   0.00451  -0.0042   0.4125   1.0000
   4.750   0.5784   0.01125   0.00474  -0.0032   0.3743   1.0000
   5.000   0.6002   0.01163   0.00502  -0.0022   0.3348   1.0000
   5.250   0.6217   0.01208   0.00533  -0.0011   0.2931   1.0000
   5.500   0.6428   0.01259   0.00570  -0.0001   0.2498   1.0000
   5.750   0.6634   0.01319   0.00613   0.0009   0.2066   1.0000
   6.000   0.6835   0.01389   0.00665   0.0021   0.1660   1.0000
   6.250   0.7027   0.01471   0.00731   0.0033   0.1316   1.0000
   6.500   0.7216   0.01560   0.00805   0.0046   0.1033   1.0000
   6.750   0.7409   0.01643   0.00883   0.0059   0.0808   1.0000
   7.000   0.7583   0.01750   0.00981   0.0074   0.0640   1.0000
   7.250   0.7761   0.01855   0.01087   0.0090   0.0508   1.0000
   7.500   0.7921   0.01983   0.01212   0.0107   0.0409   1.0000
   7.750   0.8106   0.02087   0.01331   0.0123   0.0352   1.0000
   8.000   0.8238   0.02318   0.01558   0.0143   0.0311   1.0000
   8.250   0.8437   0.02407   0.01667   0.0157   0.0283   1.0000
   8.500   0.8621   0.02518   0.01789   0.0170   0.0257   1.0000
   8.750   0.8791   0.02682   0.01961   0.0184   0.0241   1.0000
   9.000   0.8939   0.02966   0.02261   0.0198   0.0230   1.0000
   9.250   0.9048   0.03332   0.02662   0.0216   0.0225   1.0000
   9.500   0.9156   0.03582   0.02946   0.0235   0.0223   1.0000
   9.750   0.9219   0.03870   0.03271   0.0255   0.0221   1.0000
  10.000   0.9232   0.04204   0.03643   0.0277   0.0222   1.0000
  10.250   0.9187   0.04581   0.04052   0.0299   0.0223   1.0000
  10.500   0.9125   0.04994   0.04491   0.0317   0.0226   1.0000
  10.750   0.9049   0.05220   0.04737   0.0342   0.0228   1.0000
  11.000   0.8940   0.05457   0.04992   0.0361   0.0230   1.0000
  11.250   0.8816   0.05729   0.05285   0.0367   0.0233   1.0000
  11.500   0.8582   0.06189   0.05773   0.0353   0.0238   1.0000
  11.750   0.8208   0.06981   0.06597   0.0299   0.0246   1.0000
<< Back to E10(08%) (e228-il)

Polar data table (+)

Polar graphs


<< Back to E10(08%) (e228-il)