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E209 (13.72%) (e209-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E209 (13.72%) (e209-il)
Reynolds number: 50,000
Max Cl/Cd: 31.18 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e209-il-50000-n5.txt
Download as CSV file: xf-e209-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E209  (13.72%)                                  
  
 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  -0.4948   0.10128   0.09404  -0.0395   1.0000   0.0506
 -11.250  -0.5064   0.09404   0.08690  -0.0432   1.0000   0.0504
 -11.000  -0.5239   0.08622   0.07911  -0.0478   1.0000   0.0500
 -10.750  -0.5443   0.07885   0.07175  -0.0523   1.0000   0.0492
 -10.500  -0.5699   0.07185   0.06472  -0.0568   1.0000   0.0484
 -10.250  -0.5956   0.06620   0.05898  -0.0597   1.0000   0.0476
 -10.000  -0.6196   0.06201   0.05469  -0.0602   1.0000   0.0472
  -9.750  -0.6418   0.05874   0.05129  -0.0584   1.0000   0.0475
  -9.500  -0.6565   0.05556   0.04791  -0.0566   1.0000   0.0481
  -9.250  -0.6666   0.05250   0.04460  -0.0545   1.0000   0.0489
  -9.000  -0.6725   0.04949   0.04127  -0.0522   1.0000   0.0500
  -8.750  -0.6741   0.04653   0.03790  -0.0499   1.0000   0.0512
  -8.500  -0.6702   0.04373   0.03471  -0.0476   1.0000   0.0524
  -8.250  -0.6596   0.04148   0.03242  -0.0459   1.0000   0.0540
  -8.000  -0.6492   0.03977   0.03060  -0.0441   1.0000   0.0571
  -7.750  -0.6381   0.03796   0.02854  -0.0421   1.0000   0.0609
  -7.500  -0.6246   0.03607   0.02634  -0.0401   1.0000   0.0645
  -7.250  -0.6109   0.03449   0.02482  -0.0382   1.0000   0.0679
  -7.000  -0.5975   0.03314   0.02335  -0.0361   1.0000   0.0729
  -6.750  -0.5853   0.03185   0.02199  -0.0339   1.0000   0.0793
  -6.500  -0.5740   0.03071   0.02081  -0.0317   1.0000   0.0870
  -6.250  -0.5638   0.02956   0.01967  -0.0293   1.0000   0.0949
  -6.000  -0.5543   0.02852   0.01862  -0.0269   1.0000   0.1073
  -5.750  -0.5454   0.02753   0.01769  -0.0247   1.0000   0.1230
  -5.500  -0.5108   0.02604   0.01638  -0.0276   0.9884   0.1636
  -5.250  -0.4774   0.02458   0.01528  -0.0304   0.9759   0.2254
  -5.000  -0.4453   0.02348   0.01461  -0.0324   0.9628   0.3064
  -4.750  -0.4131   0.02312   0.01455  -0.0336   0.9492   0.3884
  -4.500  -0.3800   0.02309   0.01448  -0.0346   0.9356   0.4514
  -4.250  -0.3464   0.02311   0.01438  -0.0354   0.9228   0.4975
  -4.000  -0.3109   0.02311   0.01423  -0.0365   0.9115   0.5341
  -3.750  -0.2767   0.02307   0.01406  -0.0373   0.8997   0.5645
  -3.500  -0.2442   0.02300   0.01384  -0.0378   0.8874   0.5913
  -3.250  -0.2117   0.02292   0.01365  -0.0381   0.8757   0.6139
  -3.000  -0.1784   0.02279   0.01335  -0.0387   0.8650   0.6364
  -2.750  -0.1450   0.02265   0.01310  -0.0392   0.8544   0.6558
  -2.500  -0.1157   0.02254   0.01286  -0.0391   0.8422   0.6735
  -2.250  -0.0858   0.02242   0.01263  -0.0391   0.8308   0.6906
  -2.000  -0.0542   0.02228   0.01236  -0.0394   0.8207   0.7073
  -1.750  -0.0244   0.02215   0.01212  -0.0395   0.8099   0.7234
  -1.500   0.0027   0.02207   0.01195  -0.0391   0.7984   0.7391
  -1.250   0.0315   0.02199   0.01178  -0.0390   0.7883   0.7549
  -1.000   0.0620   0.02188   0.01157  -0.0392   0.7790   0.7709
  -0.750   0.0880   0.02187   0.01151  -0.0387   0.7679   0.7876
  -0.500   0.1171   0.02185   0.01144  -0.0388   0.7585   0.8051
  -0.250   0.1491   0.02181   0.01134  -0.0392   0.7496   0.8226
   0.000   0.1792   0.02188   0.01140  -0.0396   0.7395   0.8417
   0.250   0.2151   0.02188   0.01134  -0.0409   0.7314   0.8621
   0.500   0.2515   0.02198   0.01141  -0.0425   0.7217   0.8833
   0.750   0.2925   0.02208   0.01148  -0.0452   0.7128   0.9048
   1.000   0.3368   0.02214   0.01148  -0.0484   0.7045   0.9272
   1.250   0.3814   0.02230   0.01162  -0.0522   0.6949   0.9499
   1.500   0.4306   0.02231   0.01157  -0.0566   0.6874   0.9719
   1.750   0.4769   0.02248   0.01175  -0.0611   0.6774   0.9966
   2.000   0.4955   0.02270   0.01191  -0.0603   0.6695   1.0000
   2.250   0.5108   0.02301   0.01218  -0.0587   0.6611   1.0000
   2.500   0.5275   0.02339   0.01251  -0.0572   0.6530   1.0000
   2.750   0.5474   0.02372   0.01280  -0.0561   0.6454   1.0000
   3.000   0.5651   0.02418   0.01326  -0.0548   0.6370   1.0000
   3.250   0.5876   0.02452   0.01359  -0.0540   0.6298   1.0000
   3.500   0.6055   0.02507   0.01417  -0.0527   0.6214   1.0000
   3.750   0.6297   0.02540   0.01449  -0.0521   0.6144   1.0000
   4.000   0.6472   0.02603   0.01518  -0.0508   0.6057   1.0000
   4.250   0.6727   0.02633   0.01553  -0.0503   0.5990   1.0000
   4.500   0.6893   0.02704   0.01632  -0.0489   0.5898   1.0000
   4.750   0.7166   0.02729   0.01660  -0.0486   0.5833   1.0000
   5.000   0.7318   0.02807   0.01750  -0.0470   0.5734   1.0000
   5.250   0.7569   0.02840   0.01791  -0.0464   0.5659   1.0000
   5.500   0.7756   0.02900   0.01862  -0.0452   0.5562   1.0000
   5.750   0.7946   0.02960   0.01933  -0.0440   0.5466   1.0000
   6.000   0.8230   0.02968   0.01948  -0.0435   0.5384   1.0000
   6.250   0.8379   0.03040   0.02039  -0.0418   0.5269   1.0000
   6.500   0.8569   0.03090   0.02102  -0.0405   0.5161   1.0000
   6.750   0.8822   0.03101   0.02123  -0.0396   0.5059   1.0000
   7.000   0.9045   0.03122   0.02157  -0.0384   0.4944   1.0000
   7.250   0.9212   0.03166   0.02220  -0.0367   0.4813   1.0000
   7.500   0.9391   0.03198   0.02268  -0.0350   0.4679   1.0000
   7.750   0.9574   0.03219   0.02304  -0.0332   0.4536   1.0000
   8.000   0.9755   0.03233   0.02331  -0.0314   0.4384   1.0000
   8.250   0.9935   0.03239   0.02350  -0.0295   0.4221   1.0000
   8.500   1.0107   0.03242   0.02366  -0.0274   0.4047   1.0000
   8.750   1.0175   0.03304   0.02445  -0.0246   0.3851   1.0000
   9.000   1.0278   0.03340   0.02490  -0.0219   0.3645   1.0000
   9.250   1.0337   0.03397   0.02554  -0.0189   0.3426   1.0000
   9.500   1.0379   0.03463   0.02620  -0.0158   0.3195   1.0000
   9.750   1.0387   0.03572   0.02730  -0.0129   0.2951   1.0000
  10.000   1.0396   0.03697   0.02848  -0.0103   0.2703   1.0000
  10.250   1.0390   0.03853   0.02994  -0.0080   0.2465   1.0000
  10.500   1.0359   0.04058   0.03192  -0.0062   0.2239   1.0000
  10.750   1.0328   0.04282   0.03401  -0.0046   0.2043   1.0000
  11.000   1.0294   0.04535   0.03647  -0.0035   0.1860   1.0000
  11.250   1.0260   0.04804   0.03912  -0.0027   0.1693   1.0000
  11.500   1.0236   0.05079   0.04182  -0.0020   0.1549   1.0000
  11.750   1.0212   0.05364   0.04464  -0.0016   0.1416   1.0000
  12.000   1.0195   0.05653   0.04749  -0.0012   0.1299   1.0000
  12.250   1.0189   0.05935   0.05024  -0.0009   0.1197   1.0000
  12.500   1.0184   0.06235   0.05334  -0.0009   0.1097   1.0000
  12.750   1.0188   0.06536   0.05642  -0.0008   0.1011   1.0000
  13.000   1.0207   0.06806   0.05900  -0.0006   0.0940   1.0000
  13.250   1.0204   0.07144   0.06269  -0.0009   0.0868   1.0000
  13.500   1.0234   0.07416   0.06530  -0.0008   0.0809   1.0000
  13.750   1.0220   0.07795   0.06940  -0.0014   0.0756   1.0000
  14.000   1.0232   0.08107   0.07255  -0.0018   0.0708   1.0000
  14.250   1.0242   0.08463   0.07626  -0.0022   0.0671   1.0000
  14.500   1.0187   0.08936   0.08129  -0.0035   0.0640   1.0000
  14.750   1.0139   0.09387   0.08596  -0.0049   0.0613   1.0000
  15.000   1.0209   0.09615   0.08808  -0.0050   0.0575   1.0000
  15.250   1.0064   0.10271   0.09499  -0.0079   0.0564   1.0000
  15.500   0.9891   0.11014   0.10271  -0.0116   0.0556   1.0000
  15.750   0.9685   0.11864   0.11146  -0.0161   0.0553   1.0000
  16.000   0.9424   0.12910   0.12213  -0.0221   0.0554   1.0000
  16.250   0.9132   0.14142   0.13456  -0.0293   0.0559   1.0000
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